Michael Papadakis and Kuohsing E. Hung

Wichita State University, Wichita, Kansas

Giao T. Vu

Boeing Airplane Company, Wichita, Kansas

Hsiung Wei Yeong

Wichita State University, Wichita, Kansas

Colin S. Bidwell

Glenn Research Center, Cleveland, Ohio

Marlin D. Breer

Boeing Airplane Company, Wichita, Kansas

Timothy J. Bencic

Glenn Research Center, Cleveland, Ohio

Experimental Investigation of Water Droplet

Impingement on Airfoils, Finite Wings,

and an S-Duct Engine Inlet

NASA/TM—2002-211700

October 2002
The NASA STI Program Office . . . in Profile

Since its founding, NASA has been dedicated to

the advancement of aeronautics and space

science. The NASA Scientific and Technical

Information (STI) Program Office plays a key part

in helping NASA maintain this important role.

The NASA STI Program Office is operated by

Langley Research Center, the Lead Center for

NASA’s scientific and technical information. The

NASA STI Program Office provides access to the

NASA STI Database, the largest collection of

aeronautical and space science STI in the world.

The Program Office is also NASA’s institutional

mechanism for disseminating the results of its

research and development activities. These results

are published by NASA in the NASA STI Report

Series, which includes the following report types:

• TECHNICAL PUBLICATION. Reports of

completed research or a major significant

phase of research that present the results of

NASA programs and include extensive data

or theoretical analysis. Includes compilations

of significant scientific and technical data and

information deemed to be of continuing

reference value. NASA’s counterpart of peerreviewed formal professional papers but

has less stringent limitations on manuscript

length and extent of graphic presentations.

• TECHNICAL MEMORANDUM. Scientific

and technical findings that are preliminary or

of specialized interest, e.g., quick release

reports, working papers, and bibliographies

that contain minimal annotation. Does not

contain extensive analysis.

• CONTRACTOR REPORT. Scientific and

technical findings by NASA-sponsored

contractors and grantees.

• CONFERENCE PUBLICATION. Collected

papers from scientific and technical

conferences, symposia, seminars, or other

meetings sponsored or cosponsored by

NASA.

• SPECIAL PUBLICATION. Scientific,

technical, or historical information from

NASA programs, projects, and missions,

often concerned with subjects having

substantial public interest.

• TECHNICAL TRANSLATION. Englishlanguage translations of foreign scientific

and technical material pertinent to NASA’s

mission.

Specialized services that complement the STI

Program Office’s diverse offerings include

creating custom thesauri, building customized

databases, organizing and publishing research

results . . . even providing videos.

For more information about the NASA STI

Program Office, see the following:

• Access the NASA STI Program Home Page

at http://www.sti.nasa.gov

• E-mail your question via the Internet to

help@sti.nasa.gov

• Fax your question to the NASA Access

Help Desk at 301–621–0134

• Telephone the NASA Access Help Desk at

301–621–0390

• Write to:

 NASA Access Help Desk

 NASA Center for AeroSpace Information

 7121 Standard Drive

 Hanover, MD 21076
Michael Papadakis and Kuohsing E. Hung

Wichita State University, Wichita, Kansas

Giao T. Vu

Boeing Airplane Company, Wichita, Kansas

Hsiung Wei Yeong

Wichita State University, Wichita, Kansas

Colin S. Bidwell

Glenn Research Center, Cleveland, Ohio

Marlin D. Breer

Boeing Airplane Company, Wichita, Kansas

Timothy J. Bencic

Glenn Research Center, Cleveland, Ohio

Experimental Investigation of Water Droplet

Impingement on Airfoils, Finite Wings,

and an S-Duct Engine Inlet

NASA/TM—2002-211700

October 2002

National Aeronautics and

Space Administration

Glenn Research Center
Acknowledgments

Funding for this work was provided by NASA through NASA Glenn Research Grants NAG3–1775 and

NAG3–1985. The authors would like to thank the following NASA Glenn personnel: Tom Bond, Chief,

Icing Branch, for his support, John R. Oldenburg and Robert F. Ide for performing droplet size and distribution as

well as LWC measurements during the impingement tests and for their useful comments and suggestions, the IRT

personnel for their extensive support with the impingement tests, Dave Sheldon for his engineering support with

the wind tunnel models, Harold E. Addy and Charlie Andracchio for their assistance with the surface pressure

measurements, Howard Broughton and co-op student Joel Feldman for their contributions to the development of

the CCD data reduction system. The support received from Victor Canacci, NYMA, during the uniformity tests is

also acknowledged. The authors would like to thank Frank Lynch, Abdi Khodadoust, Kichio Ishimitsu, and

Anil Shah of the Boeing Company for making the three-element high lift wing model available for testing.

Thanks are also due to: Baily Vittal, Katharine Treml, and Brian Treml of the Allison Advanced Development

Company for providing the S-duct and for their support during the impingement tests; Mike Hinson and

Reuben Chandrasecharan of the Bombardier/Learjet Company for providing the 25 percent and full-scale

business jet tail models. Finally, the extensive contributions of Art Porter, Arief Rachman, Wadii Benjilany, and

Michael Davis, Wichita State University, to this project are acknowledged

Available from

NASA Center for Aerospace Information

7121 Standard Drive

Hanover, MD 21076

National Technical Information Service

5285 Port Royal Road

Springfield, VA 22100

Available electronically at http://gltrs.grc.nasa.gov

The Aerospace Propulsion and Power Program at

NASA Glenn Research Center sponsored this work.
Experimental Investigation of Water Droplet Impingement 

on Airfoils, Finite Wings, and an S-Duct Engine Inlet

Michael Papadakis and Kuohsing E. Hung 

Wichita State University 

Wichita, Kansas 

Giao T. Vu 

Boeing Airplane Company 

Wichita, Kansas 

Hsiung Wei Yeong 

Wichita State University 

Wichita, Kansas 

Colin S. Bidwell 

National Aeronautics and Space Administration 

Glenn Research Center 

Cleveland, Ohio 

Marlin D. Breer 

Boeing Airplane Company 

Wichita, Kansas 

Timothy J. Bencic 

National Aeronautics and Space Administration 

Glenn Research Center 

Cleveland, Ohio 

Abstract

Validation of trajectory computer codes, for icing analysis, requires experimental 

water droplet impingement data for a wide range of aircraft geometries as well as flow 

and icing conditions. This report presents improved experimental and data reduction 

methods for obtaining water droplet impingement data and provides a comprehensive 

water droplet impingement database for a range of test geometries including an MS(1)-

0317 airfoil, a GLC-305 airfoil, an NACA 652-415 airfoil, a commercial transport tail 

section, a 36-inch chord natural laminar flow NLF(1)-0414 airfoil, a 48-inch NLF(1)-0414 

section with a 25% chord simple flap, a state-of-the-art three-element high lift system, a 

NACA 64A008 finite span swept business jet tail, a full-scale business jet horizontal tail 

section, a 25%-scale business jet empennage, and an S-duct turboprop engine inlet. 

The experimental results were obtained at the NASA Glenn Icing Research Tunnel (IRT) 

for spray clouds with median volumetric diameter (MVD) of 11, 11.5, 21, 92 and 94 

microns and for a range of angles of attack. The majority of the impingement 

experiments were conducted at an air speed of 175 mph corresponding to a Reynolds 

NASA/TM—2002-211700 1
number of approximately 1.6 million per foot. The maximum difference of repeated tests 

from the average ranged from 0.24% to 12% for most of the experimental results 

presented. This represents a significant improvement in test repeatability compared to 

previous experimental studies. The increase in test repeatability was attributed to 

improvements made to the experimental and data reduction methods. Computations 

performed with the LEWICE-2D, and LEWICE-3D computer codes for all test 

configurations are presented in this report. For the test cases involving median 

volumetric diameters of 11 and 21 microns, the correlation between the analytical and 

experimental impingement efficiency distributions was good. For the median volumetric 

diameters of 92 and 94-micron cases, however, the analysis produced higher 

impingement efficiencies and larger impingement limits than the experiment. It is 

speculated that this discrepancy is due to droplet splashing and breakup experienced by 

large droplets during impingement. 

	

	

Ice accretion on critical aerodynamic surfaces can significantly degrade aircraft 

performance and safety. Ice protection systems are employed on most commercial 

aircraft to reduce or eliminate the adverse effects of ice accretion. The design of ice 

protection systems requires knowledge of local and total droplet impingement intensities 

in order to determine energy levels per unit area for ice protection. In addition, the water 

impingement limits are needed for determining the extent of the surface area to be 

protected. A number of trajectory computer codes have been developed over the years 

for predicting water impingement characteristics of internal and external aerodynamic 

surfaces. The application of these codes to icing analysis for ice protection system 

design and certification requires validation against experimental data. 

The first experimental water impingement database was developed by the 

National Advisory Committee for Aeronautics (NACA) in the 1950's using a dye tracer 

technique. In 1984, a research program was initiated to develop improved experimental 

and data reduction methods for measuring water impingement and to obtain 

experimental impingement data for a range of modern wings and engine inlets. This 

research program was sponsored by the National Aeronautics and Space Administration 

(NASA) and by the Federal Aviation Administration (FAA) and was conducted by 

personnel from the Wichita State University (WSU) and the Boeing Company. The 

program included two major tunnel entries and analysis of the extensive data was 

completed in 1993. 

A peer review of NASA icing research activities conducted in 1994 and results 

from an industry survey conducted in 1995 indicated that additional experimental water 

droplet impingement data were needed, including data for supercooled large droplet 

(SLD) conditions which were not available. To address the concerns of its industrial 

partners, the Icing Technology Branch at NASA Glenn Research Center awarded a 

research grant to Wichita State University (WSU) in 1996 to begin work on modernizing 

and expanding the water droplet impingement database. The accomplishments of this 

new research program, which was completed in 2000, are summarized below: 

NASA/TM—2002-211700 2
1. Significant improvements were made to the experimental method including 

automation of the WSU 12-nozzle spray system and development of a new laser 

sheet method for setting cloud uniformity. 

2. Extensive experiments were conducted to identify the effect of key experimental 

parameters on the repeatability of the impingement results. 

3. A new, very efficient data reduction method based on a CCD array camera was 

developed for extracting the raw experimental impingement data from the dye-laden 

blotter strips. 

4. Experiments were performed to assess the accuracy of the new data reduction 

method and extensive comparisons were made with results obtained using the laser 

reflectometer developed in the 1980's. 

5. Experimental impingement data were obtained for six two-dimensional airfoils, a 

modern high lift system, three finite swept tails and an S-duct engine inlet. Data were 

obtained for median volumetric diameters of 11, 11.5, 21, 92 and 94 microns. 

6. Correlation of the experimental impingement data with analysis data obtained with 

the LEWICE-2D and LEWICE-3D computer codes was performed. 

Nomenclature 

AOA Angle of Attack 

BJ Business Jet 

BJE Business Jet Empennage 

CCD Charge-Coupled Device 

DAQ Data Acquisition 

DIO Digital Input Output 

FAA Federal Aviation Administration 

FS Full-Scale 

FSSP Forward Scattering Spectrometer Probe 

IRT Icing Research Tunnel 

LE Leading Edge 

LWC Liquid Water Content 

MAC Mean Aerodynamic Chord 

MVD Median Volumetric Diameter 

OAP Optical Array Probe 

PDPA Phase Doppler Particle Analyzer 

RCM Reference Collector Mechanism 

PC Personal Computer 

SLD Supercooled Large Droplets 

SSR Solid State Relay 

TE Trailing Edge 

WRP Wing Reference Plane 

WSU Wichita State University 

Af Frontal area of a body projected parallel to freestream velocity direction 

A∞ Area perpendicular to freestream direction, defined by the tangent 

trajectories 

NASA/TM—2002-211700 3
c Model chord length 

CD Droplet drag coefficient 

Cf Nozzle flow coefficient 

d Droplet diameter 

D Droplet diameter 

Dmax Maximum droplet diameter in clouds of non-uniform droplet size 

Dmin Minimum droplet diameter in clouds of non-uniform droplet size 

DMVD Droplet diameter based on MVD 

E Total impingement efficiency in clouds of non-uniform droplet size 

g Acceleration due to gravity 

Highlight Reference point on test geometry for measuring impingement efficiency. 

For the single element airfoils and three finite swept tails tested the 

highlight was located at the leading edge (x/c=0). For the three-element 

configuration, the highlight was located at the leading edge of each 

element. For the S-duct inlet, the highlight locations are defined in Fig. 

22h. A summary of highlight locations for the models tested is provided in 

Appendix A. 

K V MVD ( ) c droplet ⋅ ⋅ ⋅ ⋅ ρ ∞ 18 μ 2 , droplet inertia parameter 

K0 K λ λs ⋅ , Modified droplet inertia parameter 

L Characteristic dimension of a body 

M Mach number of airflow relative to droplet 

M∞ Freestream Mach number of airflow 

Rec Reynolds number based on chord length 

Rev Reynolds number of airflow relative to droplet 

ReMVD Reynolds number based on MVD and free stream speed 

Rn Normalized reflectance 

S Surface distance from highlight 

Sβmax Surface distance from highlight to location of maximum impingement 

efficiency 

Su Surface distance from highlight to impingement limit on upper surface

Sl Surface distance from highlight to impingement limit on lower surface 

t Time; Airfoil thickness 

Ui Initial droplet velocity 

V Potential flow velocity dimensionless with V∞

Vi Initial potential flow velocity

V∞ Freestream airspeed 

W Water flow rate from WSU spray nozzles 

W Engine inlet mass flow 

x,y Cartesian coordinates 

xl Chordwise distance corresponding to the impingement limit on the lower 

surface 

xu Chordwise distance corresponding to the impingement limit on the upper 

surface 

α Angle of attack 

β Local impingement efficiency 

NASA/TM—2002-211700 4
∆P Pwater-Pair 

δij Kronecker delta

φ Impingement parameter ( ) MVD K 2 Re

λ True range of droplet as projectile injected into still air 

λs Range of droplet as projectile following Stokes’ law 

μ Absolute air viscosity 

ρ Air density 

ρω Density of water 

1.0 Introduction 

Aircraft flying at subsonic speeds through clouds below 8000 meters 

(approximately 26,000 ft) can be subject to ice formation on critical aerodynamic 

surfaces which can lead to deterioration of aircraft aerodynamic performance and 

handling qualities. Ice accretion results from small, supercooled droplets (droplets 

cooled below freezing), usually 5 to 50 microns in diameter, which can freeze upon 

impact with the aircraft surface. Ice protection systems are employed on most 

commercial aircraft to reduce or eliminate the adverse effects of ice accretion. The 

design of ice protection systems requires knowledge of local and total droplet 

impingement intensities in order to determine energy levels per unit area for ice 

protection. In addition, the water impingement limits are needed for determining the 

extent of the surface area to be protected. Thus, experimental water droplet 

impingement data are important to the development and certification of ice protection 

systems. 

 Experimental impingement data are also needed for the validation of trajectory 

computer codes, which play a significant role in aircraft icing analyses. A number of 

trajectory computer codes have been developed over the years for predicting the water 

impingement characteristics of internal and external aerodynamic surfaces. These 

codes are commonly used by industry as a cost-effective tool for evaluating icing 

protection requirements for aircraft components and to assist in the testing and 

certification of ice protection systems. 

Several efforts in water droplet impingement research, including the work by the 

NACA in the 1950’s and the research in the 1980’s and 1990’s, can be found in Refs. 1-

7. These efforts have generated experimental impingement data for a range of 

conditions within the current icing certification requirements. 

Recently, ice accretions resulting from supercooled large droplets (SLD) have 

become a safety concern in the aviation community. These icing conditions are outside 

the icing certification envelope as defined in Appendix C of FAR Part 25. As a result, 

regulatory authorities are currently evaluating large droplet icing effects and safety 

issues. To expand the range of application of current icing analysis codes beyond the 

NASA/TM—2002-211700 5
current icing certification envelope would require experimental impingement data for 

large droplets. 

This report includes small and large droplet impingement data for a range of 

aerodynamic surfaces. The experimental data were obtained in 1997 and in 1999 at the 

NASA Glenn Icing Research Tunnel (IRT) facility. The selection of test models and 

conditions for the impingement tests was based on an industry survey conducted in 

1995. 

2.0 Background 

The first extensive water droplet impingement database was developed by NACA 

in the 1950’s. A dye-tracer technique was developed for measuring local impingement 

efficiency on aircraft aerodynamic surfaces (Ref. 1). In this technique, water containing a 

small amount of water-soluble dye was injected in the form of droplets into the air 

stream ahead of the body by means of spray nozzles. The surface of the body was 

covered with blotter material upon which the dyed water impinged and was absorbed. At 

the point of impact and droplet absorption, a permanent dye deposit (dye trace) was 

obtained. The impingement limits were obtained directly from the rearmost dye trace on 

the absorbent material. 

Data analysis consisted of removing the dyed blotter strips from the body and 

punching out small segments of the blotter material for the determination of local 

impingement characteristics. The dye was dissolved out of each segment in a known 

quantity of water. The weight of dye in this solution was determined by the amount of 

light of a suitable wavelength transmitted through the solution by use of a calibrated 

colorimeter (colorimetric analysis). The weight of water that impinged at any surface 

location per unit time was determined from the weight of dye collected per unit area, and 

from knowledge of the original concentration of the dye in the water droplets. 

The liquid water content in the cloud was determined using an aspirating device 

(Refs. 1, 2). This device consisted essentially of a tube, which sucked in the 

approaching air and cloud droplets at the freestream velocity (inlet velocity ratio 1) so 

that both the air streamlines and droplets entered the tube along straight-line paths. The 

dyed droplets were deposited on a filter mounted within the tube, leaving a dye trace 

that could be analyzed using colorimetric analysis. The droplet size distribution was 

determined by comparing experimental local impingement rates on cylinders of different 

sizes with theoretical predictions of droplet trajectories and impingement points using a 

differential analyzer. 

Between 1955 and 1958 NACA personnel developed a water droplet 

impingement database for a wide range of cylinders, airfoils sections, bodies of 

revolution and a supersonic inlet (Refs. 1–5). Table 1 provides a selected list of test 

geometries and conditions used by NACA personnel for water droplet impingement 

testing. For most test configurations, the NACA method was sufficiently accurate. The 

NASA/TM—2002-211700 6
error in evaluating maximum local impingement efficiency varied from 10 to 25 percent 

(Refs. 1, 2). The major limitations of the NACA method included reduced spatial 

resolution and a laborious and time-consuming process for reducing the experimental 

data. In addition, the uncertainty in measuring the LWC and MVD values of the spray 

clouds used in the impingement tests was considerable. 

 In 1984, a research program was initiated to further expand and update the 

experimental water droplet impingement database and to provide much needed 

impingement data for aircraft inlets and modern wing sections. This program was 

sponsored by the NASA Glenn Research Center in Cleveland, Ohio and the FAA 

Technical Center in Atlantic City, New Jersey. The work was performed by researchers 

at Wichita State University and Boeing. During this research program, an experimental 

method similar to the one used in the early 1950's by NACA researchers was developed 

for measuring local impingement efficiency (Ref. 6). A new method for extracting the 

impingement data from the blotter strips was also developed. In this method, the amount 

of dye trace on a blotter strip obtained in a given time interval was converted into local 

impingement efficiency distribution using a laser reflectance spectroscopy method. 

Tests showed that the new data reduction method was significantly more efficient than 

the method of colorimetric analysis used in the 1950's by NACA personnel. 

 To generate the required spray clouds for the impingement tests a twelve-nozzle 

spray system was fabricated. This system was designed to have a very fast on/off 

response because the spray duration had to be very short (approximately 2–4 sec) to 

avoid saturation of the blotter paper. For the reflectance method to be accurate, dye 

penetration into the blotter paper had to be kept to a minimum. 

 The first series of impingement tests were conducted in September of 1985 in the 

NASA IRT for a period of four weeks. The geometries tested included a four-inch 

cylinder, a NACA 652-015, an MS(1)-0317 supercritical airfoil, three simulated ice 

shapes, an axisymmetric engine inlet model and a Boeing 737-300 engine inlet model. 

The configurations tested are given in Table 2. The second and final series of 

impingement tests were performed in the IRT facility during April of 1989 and lasted for 

approximately four weeks. Models tested during this phase of the research program 

included two simulated ice shapes, a Natural Laminar Flow airfoil section NLF(1)-0414F, 

an infinite span 30 degree swept MS(1)-0317 wing, a finite span 30 degree swept NACA 

0012 wing, and a Boeing 737-300 engine inlet model. Details of the test geometries and 

conditions are given in Table 3. The experimental impingement data obtained during the 

1985 and 1989 impingement tests can be found in Refs. 6 and 7. In summary, the water 

droplet impingement research program conducted between 1984 and 1993 was 

successful and considerably expanded the impingement database. 

A peer review of NASA Glenn icing research activities conducted in 1994 

indicated that additional water droplet impingement data were needed. Large droplet 

impingement data were also requested in response to a recent commuter aircraft icing 

related accident which has raised the question of the effect of ice accretion due to 

Supercooled Large Droplets (SLD) on aircraft performance and handling characteristics 

NASA/TM—2002-211700 7
(Refs. 8, 9). Preliminary studies of the effect of SLD on the ice accretion characteristics 

of a full-scale Twin-Otter wing section were reported in Ref. 10. Icing tests conducted 

with large droplets of 99 and 160 microns MVD demonstrated that an ice ridge formed 

aft of the active portion of the deicer boot. Potential adverse effects due to this ice ridge 

formation on the aerodynamic characteristics of aircraft include large loss in lift, increase 

in drag and pitching moment, and in severe cases aileron hinge moment reversal and 

aileron snatch as discussed in Ref. 11. 

Currently, the Aviation Rulemaking Advisory Committee (ARAC)Ice Protection 

Harmonization Working Group (IPHWG) is considering rulemaking addressing aircraft 

operations in SLD icing conditions. These conditions are outside the current icing 

certification envelopes. Current droplet trajectory and ice accretion computer codes are 

not validated for SLD conditions and they will need to be validated so that they can be 

used as a means of compliance (Ref. 12). Experimental data is needed to assess the 

validity and acceptability of droplet trajectory codes for SLD conditions. 

 To address the concerns of the icing community, the Icing Technology Branch at 

NASA Glenn Research Center awarded a research grant to Wichita State University 

(WSU) in 1995 to begin work on modernizing and expanding the water droplet 

impingement database. WSU and NASA conducted an industry survey in November of 

1995 to identify geometries and conditions to be considered for the next series of water 

droplet impingement tests. 

Survey participants were chosen from a database of scientists and engineers 

kept by the NASA Glenn Icing Branch. Surveys were sent to anyone who was believed 

to be interested in the goals of this program. A total of 54 surveys were sent out. About 

50% of the surveys were received back. Table 4 shows a summary of the survey 

participants by company. Table 5 provides geometries requested by industry group. 

Geometries ranged from wings, inlets, S-ducts to radomes. Conditions specified 

included drop sizes from 15 to 4,000 microns, airspeeds from 0–500 mph, a wide range 

of angles of attack and inlet mass flows. 

 Survey participants were invited to attend a workshop at NASA Glenn on 

December 8, 1995, to discuss concerns, experimental tasks and priorities, test models 

and test conditions. The workshop results were compiled and were distributed to all 

survey participants in the form of a second questionnaire for further comments and 

inputs. Responses from the second questionnaire were used to define a test matrix for 

future impingement tests in the NASA Glenn IRT facility. 

 In December of 1996, NASA awarded a second grant to WSU to improve the 

experimental method developed during the 1984 to 1993 research program and to 

develop of a more efficient reflectance method based on a CCD camera for extracting 

the impingement data from the blotter strips. In addition, extensive impingement tests 

were planned in the NASA Glenn Icing Research Tunnel with a range of twodimensional airfoils, and finite wings and a turboprop S-duct engine inlet. 

NASA/TM—2002-211700 8
The first series of the IRT impingement tests was conducted during the period of 

July 25 to September 7, 1997. The second series of impingement tests was conducted 

from January 31 to March 1, 1999. A total of 11 wind tunnel models were tested during 

these two IRT entries. Test models included six two-dimensional airfoils, a twodimensional high-lift system, three swept horizontal tails and an engine inlet S-duct. 

Tests were performed for a range of angles of attack and for median volumetric 

diameters of 11, 11.5, 21, 92 and 94 microns. The 92-94 MVD case was selected to 

provide SLD impingement data. 

Detailed descriptions of the experimental and data reduction methods used to 

generate the impingement data and all the experimental impingement data obtained 

during the 1997 and 1999 IRT entries are presented in the following sections of this 

report. 

3.0 Droplet Trajectory Equation and Impingement Parameters

 The non-dimensional form of the droplet trajectory equations and nondimensional impingement parameters that are commonly used in the presentation of 

theoretical and experimental impingement data are presented in this section. The 

dependent impingement parameters are defined for clouds with uniform and nonuniform droplet size distributions. 

3.1 Differential Equation of Particle Trajectory

 The forces acting on a small spherical droplet moving in the steady flow of air 

involve droplet drag, weight, and buoyancy (Ref. 13). The fluid dynamic drag arising 

from the relative (slip) velocity of air with respect to the droplet acts as the predominant 

force on a droplet. The development of the droplet trajectory equations is based on a 

simplified approach, taken by researchers as early as the 1940’s. In this approach, the 

quasi-steady motion of small spherical droplets moving in the steady flow of air is 

considered and it is assumed that the motion of droplets does not disturb the airflow. 

The main assumptions used in the derivation of the particle trajectory equations are 

summarized below (see Ref. 13): 

1. Single phase (air) flow about the body; flow field is not disturbed by the presence 

of droplets 

2. Quasi-steady-state approximation: at each instant and position, the steady state 

drag and other forces act on the particle 

3. The drag coefficient for stationary sphere applies 

4. Particles are assumed to be solid and spherical in shape 

5. Particles do not rotate and have no lift and no moment 

6. All drops which strike the airfoil deposit on the surface. Droplets do not 

splash/breakup during the impingement process 

7. Droplets do not interact with other droplets 

NASA/TM—2002-211700 9
8. Compressible or incompressible potential flow field of the gas phase about the 

body 

9. Viscous flow effects such as thick boundary layer formation and flow separation 

are not considered. 

Using the above assumptions and applying Newton’s second law, the nondimensional form for the particle trajectory equation is obtained: 

( ) ( ) ( )

2

i D v v i i i2

V

1 g L

24K

C Re Re V U

dt

dU

∞

− ⋅ ⋅ ⋅ − ⋅ ⋅ − = σ δ (3-1) 

where K V d 18 L 2 = ρ p ∞ μ , inertia parameter of droplet 

 d = Droplet diameter 

μ = Absolute air viscosity 

V = Freestream speed 

 t = Time, dimensionless with L/V∞

σ = ρ/ρp

, density ratio of air to particle 

L = Characteristic dimension of body

Rev = Reynolds number of airflow relative to droplet 

Ui = ith directional component of particle velocity, dimensionless with V

Vi = ith directional component of air velocity, dimensionless with V

The above mathematical model is valid for icing conditions within the intermittent and 

continuous maximum icing envelopes defined in the Federal Aviation Regulation, Part 

25, Appendix C. The maximum concentration and mean volumetric diameter (MVD) of 

droplets for these icing conditions are as follows: 

 Intermittent Maximum Continuous Maximum 

LWC 3.0 g/m3

 0.8 g/m3 

MVD 50 μm 40 μm 

For the concentrations and sizes of droplets expected to occur within icing clouds, the 

assumptions of undisturbed airflow and spherical shape (due to surface tension) of 

droplets are valid. 

 The droplet drag coefficient, CD in Eq. 3.1 is a function of the relative Reynolds 

number. It is an analytical form of the standard drag curve and the Cunningham drag 

correction factor for molecular slip and compressibility effect. The CD is given in the 

following form: 

( ) ( )

( ) v

D v

D v G M Re

C Re

C M,Re inc = (3.2) 

where 

= Dinc

C Incompressible sphere drag coefficient 

NASA/TM—2002-211700 10
G(M Rev ) = Cunningham drag correction factor 

 M = Mach number of airflow relative to droplet 

From Stokes’ law of drag, the incompressible sphere drag coefficient can be 

expressed as: 

 ( ) ( ) 













 = +

6

Re C Re C Re 1

2 3

v Dinc v DStokes v (3.3) 

where 

 ( ) v

D v Re

24 C Re = Stokes 

This equation agrees to within about 5% of the standard drag curve in the range of 

0 ≤ Rev ≤ 1000 and for particles of diameter less than or equal 1 mm. 

 The Cunningham drag correction factor was proposed by Carlson and Hoglund 

(Ref. 14) with following empirical fit to available experimental data for the ranges of 

M ≤ 0.2 and Rev ≤ 1000 : 

 B

A

Re

M G

v

=













 (3.4) 

where 

( ) ( ) [ ] 1.25Re M v v A 1 M Re 3.82 1.28e − = + +

( ) 0.88 v 4.63 0.427M 3 Re B 1 e − − − − = +

The numerator, A in Eq. 3.4 represents the drag reduction factor to account for 

the incompressible drag due to the molecular slip or rarefaction effects. The 

denominator, B in Eq. 3.4 is the additional correction to account for the Mach number 

dependence of the particle drag (compressibility) in continuum flow. 

3.1.1 Large Droplet Effects 

 A number of droplet trajectory codes have been developed over the years which 

use the trajectory equation discussed in this section. These codes have been 

extensively tested for icing conditions within the FAA, Part 25, Appendix C envelope and 

in general, have demonstrated good agreement with experimental impingement data. 

Currently, there is need to extend the application of these trajectory codes to icing 

clouds with median volumetric diameters greater than 40 μm which fall outside the 

Appendix C envelop. For large droplet clouds, some of the assumptions made in 

deriving the trajectory equation may not be valid. In addition, computation of large 

droplet impingement may require improvements to the existing numerical models to 

account for physical phenomena such as droplet splashing and breakup that have been 

observed in recent experimental impingement studies with large droplets. The impact of 

these phenomena on the simulation of the impingement characteristics of aerodynamic 

surfaces can be considerable as demonstrated in section 7 of this report where large 

NASA/TM—2002-211700 11
droplet experimental and computational impingement data are compared for a range of 

aerodynamic surfaces. 

3.2 Impingement Parameters 

 Spray cloud characteristics and droplet impingement parameters for clouds with a 

range of drop sizes are discussed below. 

3.2.1 Liquid Water Content (LWC)

 The liquid water content (LWC) of a cloud is the amount of water contained in a 

given volume of cloud. LWC is usually expressed in grams of water per cubic meter of 

cloud. LWCmax values for icing clouds according to the Appendix C icing envelopes are 

presented in section 3.1. For simulated icing clouds inside the icing tunnels, the LWC is 

controlled by the water and /or air pressures of the spray system used to create the 

spray clouds. 

3.2.2 Cloud Droplet Distribution

 The distribution of droplets in a cloud can be expressed in various forms (Ref. 6). 

Briefly, the following four types of distributions are most commonly used: 

1. Number density of droplets versus droplet diameter 

2. Percent of liquid water content versus droplet diameter 

3. Percent of liquid water content versus droplet diameter normalized to median 

volumetric diameter. 

4. Percent cumulative liquid water content versus droplet diameter normalized to 

median volumetric diameter. 

A distribution which has been employed in various analytical studies is the 

Langmuir “D”. This distribution and other similar ones were established by Langmuir 

(Ref. 15) from natural-icing cloud measurements made on Mt. Washington. The rate of 

deposition of ice on slowly rotating cylinders exposed to supercooled clouds blowing 

over the summit was correlated with that of theoretical calculations. Reference 6 

provides comparisons of Langmuir “D” distribution and the droplet distributions produced 

by the WSU spray system used in the 1985 impingement tests. A dimensionless 

Langmuir “D” distribution is shown in Fig. 1a. 

3.2.3 Median Volumetric Diameter (MVD)

 The Median Volumetric Diameter (MVD) of a droplet distribution is defined as the 

droplet diameter for which half the total liquid water content is contained in droplets 

larger than the median and half in droplets smaller than the median. Given a droplet 

distribution, the MVD can be calculated as follows: 

1. For a continuous distribution, if n(D) is the number of particles per unit 

sampling volume having diameters between D and D+dD (volumes between V

and V+dV) then DMVD can be calculated from 

NASA/TM—2002-211700 12
( )

( )

0.5

n x x dx

n x x dx

max

min

MVD

min

D

D

2

2

D

D

2

2

=

∫

∫

ω π

ω π

ρ

ρ

 (3.5) 

2. For a discrete distribution, if the particle number density is given in N discrete 

groups such that ni(Di) is the number of the particles in group i having 

diameters between D and D+dD then, Eq. 3.5 can be written as 

( )

( )

0.5

n D D

n D D

N

i 1

3

6 i i i

K

i 1

3

6 i i i

=

∑

∑

=

=

ω π

ω π

ρ

ρ

 (3.6) 

 where 

 DK = the diameter of group K, is equal to the MVD (DMVD)

 ρω = density of water, Kg/m3 

3.2.4 Local Impingement Efficiency ( β ) 

 Considering a body in a cloud with uniform droplet size distribution, the local 

impingement efficiency β for any point on the body surface is defined as the local droplet 

flux rate at the body surface normalized to the freestream flux rate. Referring to Fig. 1b, 

β is defined as the ratio of that infinitesimal area dA∞ to the corresponding impingement 

area on the body surface dAs. This definition follows from the continuity of droplet mass 

flow. 

For a continuous non-uniform cloud distribution, the impingement efficiency is 

given by the following expression 

 ∫ = t

0 t

d 1 ω

β ω

ω

β (3.7) 

where β is a function of drop size and therefore can be expressed as a function of ω, the 

liquid content for a given drop size. 

 For a discrete cloud distribution, β is defined as the weighted average of the local 

impingement efficiency values due to each droplet group in the cloud. Let ωt be the 

liquid water content of the cloud, ∆ωi be the partial liquid water content contained in the 

droplets of size (di), in the group (i) of the distribution, and N be the total number of 

discrete size droplet groups available. For a body exposed to a cloud with such a droplet 

distribution, the local impingement efficiency due to a single droplet group of size di is βi, 

where β is defined in figure 1b. The local impingement efficiency due to all N groups in 

the distribution over an infinitesimal area of the body is given by the following expression 

NASA/TM—2002-211700 13
∑

=

=

N

i 1

i i

t

1 β ∆ω

ω

β (3.8) 

3.2.5 Total Impingement Efficiency ( E ) 

 The total impingement efficiency of a three dimensional body exposed to a cloud 

of droplet distribution is defined as 

 s

S

S f

dA

A

1 E u

l

β ∫ = (3.9) 

where 

Af is the projected frontal area of the body 

dAs is an infinitesimal impingement area on the surface of the body 

Su and Sl represent the upper and lower impingement limits on the body 

3.2.6 Impingement Limits

Droplets which start out at freestream position y∞ ( Fig. 1c) with respect to a reference 

line that pass through the highlight (most forward point at α=0°) of a body downstream 

will impinge at some location on that body. As these initial freestream droplet positions 

increase in distance from the reference line they will impinge farther back along the 

surface of the body until a maximum distance y∞,max is obtained. This limiting trajectory 

is defined as the tangent trajectory to the body at point P (Fig. 1c). Any droplets starting 

at a freestream location farther from the reference line than y∞,max will miss the body 

entirely. The distance Sm measured along the body surface from the highlight of the 

body to point P is called the limit of impingement. This distance is usually expressed in 

dimensionless form by dividing Sm by the characteristic length (L) of the body. 

 For two-dimensional flow, there are two impingement limits, an upper and lower 

(for external flow, e.g., airfoil section) or an outer and inner (for partly internal flow, e.g., 

engine inlet). For three-dimensional flow, the limits of impingement may vary spanwise 

along the surface of a finite wing or circumferentially along the surface of an engine 

inlet. For a droplet distribution that varies from Dmin to Dmax, the impingement limits can 

be established for each droplet size. The maximum impingement limits are defined by 

the impingement limits of the largest droplet diameter of the distribution. 

3.2.7 Summary of Droplet Impingement Parameters

Table 6 provides a list of definitions and expressions for key non-dimensional 

parameters that affect the droplet trajectory such as droplet inertia parameter K, droplet 

modified inertia parameter K0, Reynolds number based on MVD, ReMVD, true droplet 

range λ, and independent impingement parameter φ, which represents the deviation of 

the droplet drag force from Stoke's law and is defined is such a way that the droplet 

diameter, d, has been eliminated. These non-dimensional impingement parameters are 

also useful in linking the impingement data presented in this report with early 

NASA/TM—2002-211700 14
experimental and numerical studies of airfoil water impingement characteristics (Refs. 1 

and 2). In some of these early studies, the impingement characteristics of bodies were in 

some cases presented in terms of non-dimensional impingement parameters such as K

and φ. Note that the definitions in Table 6 are based on the reference length, typically 

the airfoil chord for two-dimensional sections or the mean aerodynamic chord (MAC) for 

finite span wings. 

4.0 Experimental Method 

4.1 Wind Tunnel Facility 

The impingement tests were conducted in the NASA Glenn Icing Research 

Tunnel (IRT). The IRT is a closed-loop refrigerated wind tunnel with a 6-ft high by 9-ft 

wide by 20-ft long test section and a maximum speed of 430-mph (empty test section). A 

plan view of the IRT circuit is shown in Fig. 2. The tunnel circuit operates at or below 

atmospheric pressure, and the test section static temperature can be controlled between 

–40 °F to +40 °F. All test models were installed on the tunnel turntable using the floor 

mounting plate (See Fig. 3). A view of the IRT test section is given in Fig. 4. Two sets of 

nozzles are available in the IRT facility for generating spray clouds and include the 

standard and MOD-1 type nozzles. The basic IRT nozzle design is shown in Fig. 5. The 

IRT spray system consists of 10 spray bars with 54 nozzle locations per spray bar. Only 

129 nozzles are currently being used to generate the required icing clouds. The IRT 

spray system is capable of simulating icing clouds with MVDs in the range of 14 to 

40μm, and Liquid Water Content (LWC) of 0.3 to 3 g/m3 as shown in Figs. 6 and 7. 

Recently, a small number of large droplet calibrations have been performed permitting 

the generation of icing clouds with MVDs in the range 70 to 270 microns. Further details 

regarding the IRT facility are provided in Ref. 16. 

4.2 Test Models and Instrumentation

Details of the eleven test models used in the experimental investigation and 

related instrumentation are given below. 

4.2.1 MS(1)-0317 Airfoil

 The MS(1)-0317 airfoil is representative of modern medium speed airfoils. It was 

designed in the mid 1970’s for general aviation aircraft (Ref. 17). This two-dimensional 

airfoil was constructed out of Fiberglass skin, which was epoxied to an aluminum spar 

and aluminum ribs. The interior of the airfoil model was filled with foam. An aluminum 

plate was installed at each end of the model for mounting in the IRT test section. The 

model had a nominal span of 72 inches and a chord of 36 inches and it was mounted 

vertically in the test section. A total of 49 static pressure taps were available for this 

airfoil. These taps were located in the chordwise direction 35.5 inches above the tunnel 

floor. The MS(1)-0317 airfoil section and model installation details are given in Figs. 8a8c. Impingement data for this airfoil were obtained during the 1985 IRT impingement 

tests performed by WSU and Boeing. These data were used to verify the experimental 

set up for the 1997 and 1999 water droplet impingement tests. 

NASA/TM—2002-211700 15
4.2.2 GLC-305 Airfoil

This airfoil is representative of general aviation business jet wing sections. It was 

constructed at the NASA Glenn Research Center out of Fiberglass with two 2-inch thick 

wooden spars and seven 1-inch thick ribs as described in Ref. 18. It had 36-inch chord, 

72-inch span and 3.123-inch maximum thickness (tmax = 8.7% chord) at x/c = 0.4. The 

airfoil was instrumented with 44 static pressure taps distributed in the chordwise 

direction at a span location 33 inches above the tunnel floor. The airfoil section 

geometry and installation in the IRT test section are shown in Figs. 9a–9c. 

4.2.3 NACA 652-415 Airfoil

This airfoil is representative of general aviation wing sections. Airfoils suitable for 

low speed general aviation aircraft should have low drag and gentle stall characteristics 

with relatively high thickness ratio to keep structural weight low and to provide sufficient 

space for fuel (Ref. 19). The NACA 6-series airfoils were designed to have low profile 

drag in a limited range of lift coefficient (drag bucket). Aerodynamic performance 

characteristics for the NACA 652-415 airfoil are provided in Ref. 20. 

The single element NACA 652-415 wind tunnel model was designed and 

fabricated at Wichita State University. It was made out of aluminum, and had 72-inch 

span and 36.53-inch chord which was truncated to 36 inches during manufacturing to 

allow for sufficient trailing edge thickness for installation of a pressure port at the trailing 

edge. The maximum thickness for this airfoil was 5.486 inches (t/c = 0.15) and was 

located at approximately 40% chord. The center of rotation of the airfoil was at 50% 

chord. The airfoil was instrumented with 79 pressure taps at the mid span location which 

corresponded to the IRT centerline. Twelve additional pressure taps were placed in the 

chordwise direction one foot above and below the centerline taps (6 taps on each side) 

and nine more taps were distributed spanwise at the 70% chord station on the upper 

surface of the airfoil. The 21 additional pressure taps were used to verify that twodimensional flow was maintained for the angles of attack used in the impingement tests. 

The airfoil section geometry and installation in the IRT test section are shown in 

Figs. 10a–10c. 

4.2.4 Commercial Transport Tail Section

 This airfoil was provided by NASA Glenn Research Center and was 

representative of horizontal tail sections used in large commercial transport aircraft. The 

model was constructed out of Fiberglass skin 3/8-inch thick with two 2-inch thick wooden 

spars and seven 1-inch thick ribs (Ref. 18). The airfoil had 36-inch chord, 72-inch span 

and a maximum thickness of approximately 9% chord (3.23 inches) at x/c = 0.34. It was 

instrumented with 44 static pressure taps distributed in the chordwise direction at a span 

location 33 inches above the tunnel floor. Two thirds of the static ports were located in 

the forward 50% portion of the chord length. Figures 11a–11c show the airfoil geometry 

and model installation in the IRT test section. 

NASA/TM—2002-211700 16
4.2.5 36-in and 48-in NLF(1)-0414 Airfoils

The Natural Laminar Flow NLF(1)-0414 airfoil was designed in the early 1980’s 

for general aviation applications. Airfoil design performance features at a Reynolds 

number of 10 million and Mach number of 0.4 included lift coefficient of 0.4, drag 

coefficient of 0.0027 at an angle of attack of approximately –1°, 70% chord laminar flow 

on both surfaces, and maximum lift coefficient of 1.83 at a stall angle of attack of 17.8°

(Ref. 21). The NLF(1)-0414 airfoil had a maximum thickness to chord ratio of 0.143. The 

maximum thickness on the upper surface was 8.3% chord at x/c = 0.418 while that on 

the lower surface was 6% chord at x/c = 0.515. 

 Two NLF(1)-0414 airfoils were tested, a 36-inch single element airfoil and a 48-

inch two-element section. Both models spanned the height of the IRT test section (72 

inches). 

The 36-inch airfoil was provided by NASA Glenn and was constructed out of 

Fiberglass. The airfoil had a trailing edge thickness of 0.055 inches and it was 

instrumented with five pressure taps. The airfoil section and model installation details 

are depicted in Figs. 12a–12c. 

The 48-inch two-element airfoil shown was fabricated at WSU out of aluminum 

and had a simple 25% chord full span flap as shown in Fig. 13a. The deflection of the 

control surface was adjustable in 5-degree increments from –35° to +35°. The pivot 

location of the control surface was at x = 37.584 in, y = –0.116 in. The leading edge 

radius of the control surface was 1.584 inches and the trailing edge thickness was 0.057 

inches. The gap between the control and the main element was 0.2 inches. The 48-in 

model was instrumented with 124 pressure taps, which were distributed as shown in 

Table 7. Figures 13b–13c show the model installation in the IRT test section. 

4.2.6 NACA 64A008 Swept Tail

This was a full-scale reflection plane tail model consisting of the outboard portion 

(44% to 100% semi-span) of a general aviation business jet tail. The tail tip consisted of 

a semi-cylindrical cap. Geometry and model installation details are provided in 

Figs. 14a–14d. The model was fabricated at NASA Glenn Research Center out of 

aluminum and it was instrumented with 60 pressure taps which were equally divided 

between two spanwise stations 24 and 43 inches above the tunnel floor as shown in 

Fig. 14c. The tail airfoil was a symmetric 8% thick NACA 64A008 section and it was 

constant from root to tip. The location of maximum thickness for this airfoil section was 

at x/c = 0.39. The Mean Aerodynamic Chord (MAC) of the finite swept tail model was 

37.65 inches and was located approximately 22 inches above the tunnel floor. 

4.2.7 25%-Scale Business Jet Empennage (BJE) 

 The horizontal tail of the BJE consisted of a tapered swept planar planform (i.e., 

no twist and no dihedral) with an 8% chord thick airfoil section from root to tip. The 

location of the maximum thickness was at approximately 38% local chord. The airfoil 

section was in the streamwise direction and its chord length was 16.35 inches at the root 

and 7.04 inches at the tip. The tail sweep was 29.098 degrees at leading edge and 

NASA/TM—2002-211700 17
11.066 degrees at the trailing edge. The tail mean aerodynamic chord (MAC) was 12.31 

inches, the tail span was 51.575 inches and the tail area was 603.135 in2

. The aspect 

ratio of the horizontal tailplane was 4.4. The incidence of the horizontal tail was –8 

degrees with respect to the body axis. Thus, a body angle of attack (AOA) of +8°

corresponded to a geometric angle of attack of 0° at the tail. 

 The elevator had a leading edge sweep of 17.28 degrees with its leading edge at 

68% of local chord. The elevator hinge line was at 73.32% chord location. The elevator 

surface behind the hinge line had a geometric mean chord of 3.072-inch and a planform 

area (left + right elevators) of 152.784 in2. 

 The right side of the tail surface was instrumented with 126 pressure taps 

distributed at three spanwise locations corresponding to 25%, 55% and 85% semi-span. 

Each spanwise location had 42 static pressure ports. Fig. 15a shows the geometry of 

the airfoil section. The installation of this model in the IRT test section is shown in 

Figs. 15b–15e. 

4.2.8 Full-Scale Business Jet Horizontal Tail

 This model was a half-span full-scale version of the 25%-scale BJE horizontal tail 

described above. The full-scale tail was truncated at approximately 44.5% semi-span so 

that it could be installed in the IRT test section as a reflection plane model. The nontruncated half span full-scale horizontal tail consisted of a tapered swept planar planform 

(i.e., no twist and no dihedral) with an 8% chord thick airfoil section that remained the 

same from root to tip. The airfoil section is shown in Fig. 16a. The chord length was 65.4 

inches at the root and 28.16 inches at the tip. The maximum airfoil thickness was at 

approximately 38% local chord. The tail mean aerodynamic chord (MAC) was 49.249 

inches. The tail sweep was 29.098 degrees at the leading edge and 11.066 degrees at 

the trailing edge. The half tail span was 103.15 inches and the half tail planform area 

was 33.509 ft2

 (4825.30 in2). The aspect ratio of the non-truncated horizontal tail was 

4.4. The elevator had a leading edge sweep of 17.28 degrees and its leading edge was 

at 68% of the airfoil chord. Note that the airfoil chord varied linearly in the spanwise 

direction. The elevator hinge line was at 73% chord location and the elevator surface 

behind the hinge line had a geometric mean chord of 12.288 inch and a planform area of 

8.49 ft2

 (left elevator). For the truncated model tested, the root chord was 48.82 inch and 

the tip chord was 28.16 inch as shown in Fig. 16b. The truncated tail model had a 57-

inch span starting at 44.5% semi-span of the non-truncated model and extending to the 

tail tip (100% semi-span). Model installation details are presented in Figs. 16b and 16c. 

4.2.9 Three-Element High Lift System

 This high lift airfoil section was selected to address the needs of large transport 

airframers. The three-element section was designed in the early 1990s (Refs. 22 and 

23). It is an advanced high lift system, which is representative of modern transport wing 

designs. 

The three-element airfoil was an all aluminum model with 72 inches span and 36 

inches nested chord. The configuration consisted of a slat, a main element and a flap. 

NASA/TM—2002-211700 18
The flap and slat elements were rigged to the main element with four one-piece steel 

brackets. Only the landing configuration was considered in this investigation. For this 

case, the slat deflection was 30° leading edge down and the flap deflection was 30°

trailing edge down. Deflection of the high-lift components was set with respect to the 

main element wing reference plane (WRP) as shown in Fig. 17a. The slot size between 

the main element and the high lift components was defined in terms of the overhang 

(OH) and the gap. Overhang is the horizontal distance from the trailing edge of the 

upstream element and the leading edge of the downstream element. The overhangs for 

the slat and flap were –0.9 and +0.09 inches respectively. Gap is the minimum distance 

between the trailing edge of the upstream element and the leading edge of the 

downstream element. For the slat, the gap was 1.062 inches and for the flap it was 

0.457 inches. The installation of the three-element airfoil in the IRT test section is shown 

in Figs. 17b–17c. 

 A total of 128 static pressure taps were available on this model. These taps were 

distributed along a single chordwise row at mid-span (36 inches above the tunnel floor) 

and along three spanwise rows, two on the upper surface of the flap and one on the 

upper surface of the slat. The distribution of the pressure ports is given in Table 8. 

4.2.10 Comparison of Airfoil Sections Tested

Figures 18–21 compare the airfoil sections for the 2D and 3D wing models tested 

during the 1997 and 1999 impingement tests. Coordinates for the airfoil sections of the 

models tested can be found in Appendix B. 

4.2.11 S-duct Engine Inlet

 This model consisted of a full-scale bifurcated inlet S-duct representative of 

modern turboprop aircraft. The S-duct inlet configuration is depicted in Fig. 22a. The test 

article was actual flight hardware and was provided by the Allison Advanced 

Development Company. A bifurcated inlet of the type tested protects the engine from 

ingesting foreign objects primarily in the form of runway debris, ice, birds, etc. The 

bifurcated inlet requires scavenge air in addition to the scheduled engine airflow, thus 

causing greater mass flow rate at the highlight plane. The sizing criterion of the 

scavenge duct is based on the minimum required air flow to preclude any objects from 

entering the engine flow path at a critical operating point such as normal takeoff 

(Ref. 24). The main features of the S-duct inlet are depicted in Figs. 22b and 22c. 

Details of the inlet cross-section are provided in Figs. 22d, 22e and 22f. As shown in 

Figs. 22d–22e the inlet three-dimensional shape is a combination of two-dimensional 

elliptical cross-sections that are stacked on a three-dimensional spine line. The 

complete geometry definition for this model is available in electronic format from NASA 

Glenn Research Center. The installation of the inlet in the IRT test section is shown in 

Fig. 22g. Blotter strip locations for this model are provided in Fig. 22h. 

The inlet was instrumented with an array of 30 static pressure taps. Four static 

pressure taps were installed circumferentially at four axial locations in the duct upstream 

of the splitter nose. An additional four static taps were placed circumferentially near the 

NASA/TM—2002-211700 19
engine inlet plane. The remaining 10 taps were located on the splitter nose and along 

the lower wall of the scavenge duct. 

The main inlet mass flow was simulated and recorded using the IRT mass flow 

system. To determine the scavenge duct flow a calibrated Dantec Flow Master Probe 

type 54N60 was provided by the Allison Company. The Dantec probe used was a 

temperature compensated thermal anemometer probe with an accuracy of ±2.5%. 

Tunnel airspeeds and inlet mass flow conditions used during the impingement 

tests of the S-duct engine inlet are summarized below: 

Tunnel Air 

Speed 

mph 

Main Inlet Flow 

(Core Flow) 

lbm/s 

Scavenge Duct Flow 

lbm/s 

Capture Area Ratio 

(Includes scavenge flow) 

130 23 1.57 ± 0.04 0.84 

170 23 2.08 ± 0.05 0.65 

 

4.3 Dye Tracer Method 

The dye-tracer technique was initially developed by NACA (Ref. 1) and was 

modified by Papadakis et al. (Ref. 6). The modified dye-tracer method was used in the 

1997 and 1999 IRT impingement tests. In this method, distilled water containing a 

known concentration of blue dye (0.3g of FD&C Blue No. 1 dye per 1 liter of water) was 

injected into the air stream of the IRT in the form of a droplet spray cloud using a 

specially designed 12-nozzle spray system. The test model was covered with thin strips 

of blotter paper (James River Paper Company Verigood 100# Blotting Paper) in areas of 

interest and was exposed to the spray cloud. The amount of dye-mass per unit area of 

blotter strip obtained in a given time interval was measured using reflectance 

spectroscopy. The water impingement characteristics of a test model were obtained 

from the concentration and location of the dye distribution on the blotter paper. 

4.4 Spray System 

All 1997 and 1999 impingement tests were conducted using a twelve-nozzle 

spray system developed by personnel at Wichita State University. The IRT spray system 

was not used in this study because it was not designed for the short duration sprays 

(typically 2–18 seconds) required to prevent saturation of the blotter paper used in the 

dye tracer method. 

The WSU spray system was originally developed in 1985 but it was significantly 

modified for the 1997 and 1999 impingement tests. The system was designed to use the 

standard or MOD-1 IRT spray nozzles shown in Fig. 5. Details of the original WSU spray 

system can be found in Ref. 6. Briefly, the original system developed in 1985 provided 

blue dye solution under pressure from a high pressure supply tank to each of the 12 

nozzles via high-pressure rubber hoses as shown in Fig. 23. Pressure for the supply 

tank was obtained from a 125-psig airline, and was set to the required level using a 

mechanical pressure regulator. A separate 100-psig high mass flow air source 

(atomizing air manifold) provided air to the nozzle assemblies for atomizing the water. 

NASA/TM—2002-211700 20
The atomizing air pressure was set by a mechanical pressure regulator. Fast acting 

solenoid valves were used to turn the spray on and off. During testing, the main air 

supply solenoid was turned on several seconds before the spray was initiated to allow 

the air pressure to stabilize. Next, the 12 water solenoid valves were turned on and a 

spray cloud was produced. The median volumetric diameter (MVD) of the spray cloud 

was set by varying the air-to-water pressure ratio. The duration of the spray was 

controlled by a timer developed to turn on and off the air and water solenoid valves. 

System pressure adjustments and monitoring were done manually and as a result, 

during the 1985 and 1989 tests it was difficult to maintain consistent performance 

between sprays. 

One of the main goals of the research effort described in this report was to 

improve the repeatability of the experimental impingement data which in previous 

experimental studies was found to exhibit considerable variation. Studies conducted by 

the WSU/Boeing research group showed that spray system consistency had a large 

effect on the repeatability and quality of the experimental impingement data. Thus, a 

significant effort was directed during this new research program in improving and 

monitoring spray system performance. 

A number of electronic pressure transducers were added to the spray system at 

strategic locations to monitor the air and water pressures during each test. The pressure 

transducer selected for monitoring water pressure was the SETRA 206. A pressure 

transducer was installed in each water line just upstream of the nozzle and also at the 

water tank. The pressure of the atomizing air was measured at the regulator with a 

SETRA 204 transducer. In addition, three SETRA 206 transducers were used to monitor 

atomizing air pressures at selected nozzles. These transducers were added to the 

longest airline corresponding to each group of four nozzles. Pressure transducer 

information is provided in Table 9. Prior to each IRT test entry, the NASA Glenn flow 

calibration lab tested and calibrated all the pressure transducers used in the WSU spray 

system. 

A sensitive flow meter was added to the spray system to monitor water volume 

flow rate. This instrument measured the water volume flow rates in the range 0.02 to 1 

gallon per minute with an accuracy of 0.2% full scale (FS). This flow meter was also 

calibrated by the NASA Glenn flow calibration lab. 

The pressure regulators for setting the tank water pressure and the nozzle air 

pressure were modified so that the pressures could be set remotely from the tunnel 

control room. A miniature Electro-pneumatic transducer was added to each pressure 

regulator and was used to adjust and maintain the required air and water pressure levels 

in the spray system. During the 1999 IRT test, an automatic feedback control was 

incorporated in both the water and air pressure regulating units. The desired pressure 

levels for both air and water could be pre-set into the spray system control program to 

enhance the accuracy and repeatability of the spray system performance. 

NASA/TM—2002-211700 21
The NASA Glenn Standard nozzles used in the 1985 and 1989 impingement 

tests were replaced with the NASA Glenn MOD-1 nozzles. This was done for two 

reasons. First, the MOD-1 nozzles have a lower flow rate (approximately 1/3) for a given 

air pressure and delta pressure (Pwater–Pair) than the standard nozzles so that longer 

spray times could be achieved without saturating the blotter strips. Longer spray times 

are desirable because they result in more stable sprays. Second, large MVD calibration 

data were available for these nozzles. One of the objectives of the 1997 and 1999 

impingement tests was to produce data for MVD sizes of the order of 100 μm. 

A new stainless steel pressure tank with 30-gallon capacity was installed. The 

new larger capacity tank replaced the 9-gallon aluminum tank used previously. A set of 

12 brackets were designed and built for mounting the twelve-nozzle spray system to the 

new IRT spray bars. The new brackets allowed for a more precise installation of the 12 

nozzle assemblies. The installation of the WSU spray system in the IRT facility for 1997 

impingement tests, and the location of the twelve-nozzle spray system on the IRT spray 

bars as well as the tabulated coordinates of each spray nozzle with respect to the IRT 

spray bars are shown in Figs. 24–25. The locations of the WSU spray nozzles for the 

1999 impingement tests are given in Figs. 26–27. A close up of one of the WSU nozzle 

assemblies is provided in Fig. 28. The stainless steel pressure tank for storing the dyed 

solution and the main air and water pressure lines and the air and water pressure 

regulators are shown in Figs. 29–31a. 

The improved twelve-nozzle spray system is shown in Fig. 31b. This system was 

assembled and tested extensively at WSU before it was shipped to NASA Glenn for the 

water droplet impingement tests. During the impingement tests at the NASA Glenn IRT 

facility, several detailed analyses of recorded spray system parameters were performed. 

The results showed that the system was capable of maintaining air and water pressures 

to within ±1 psi from the required settings as demonstrated in Tables 10a and 10b. 

Note that the IRT water spray system was not used for the impingement tests. 

However, during the 1997 impingement tests, IRT spray bar air was used to enhance 

cloud uniformity. In addition, during the 1997 and 1999 impingement tests, the IRT spray 

bars were activated periodically between impingement tests to maintain the required 

relative humidity level in the tunnel air stream. 

4.5 Spray System Data Acquisition and Control 

A personal computer system with related hardware and software was developed 

to control and monitor the performance of the spray system and to store and analyze 

spray system performance parameters. This system consisted of a Pentium 100Mhz PC 

system with a data acquisition (DAQ) board, and a digital I/O (DIO) board, thirteen (13) 

solid-state relay (SSR) digital signal conditioning modules installed on two backplane 

boards, a transducer control panel, a shielded I/O connector block (SCB) and a cable 

adapter board. A schematic of the main hardware units is given in Fig. 32. The DAQ 

board was used to read and process the signals from all transducers. This board had 32 

input differential channels and a sampling rate capability of up to 500,000 samples per 

second. The DIO board was a high-speed, 32 bit parallel digital I/O ISA interface. This 

NASA/TM—2002-211700 22
board was used to turn on selected SSR relay units, which in turn activated the 

associated solenoid valves of the spray system. Each of the twelve nozzle assemblies 

had one solenoid valve. In addition, a solenoid valve was installed on the main air 

supply, which provided high-pressure air for atomizing the water sprays from the twelve 

nozzles. 

The control software was developed using LabVIEW, a graphical programming 

language for data acquisition and control, data analysis and data presentation. The 

LabVIEW software provided a Windows driven menu system for controlling and 

monitoring the performance of the spray system. The user could select any combination 

of nozzles and transducers from the windows menu, specify spray time duration, plot the 

transducer signals in real time, and store a range of impingement test parameters as 

well as other information related to each test. All test parameters and transducer 

voltages were written out to a Microsoft Excel file at the end of each test. 

During an impingement test the system software activated the solenoid valves by 

sending a command to the DIO board. Data from the DAQ board were recorded at 

regular time intervals for the complete duration of the spray. The sampling rate varied 

from approximately 9 to 18 points per second depending on spray duration. For long 

sprays, the lower sampling rate was used. This was done to keep the size of the output 

files to a manageable level. 

4.6 Cloud Uniformity 

Cloud uniformity is critical to obtaining repeatable and accurate impingement 

data. The three main parameters involved in the description of a spray cloud are droplet 

size, droplet distribution and LWC. Of these three parameters, LWC distribution is the 

most difficult to control. Extensive tests were conducted to set the location of the twelve 

spray nozzles so as to obtain a 2-ft high by 3-ft wide uniform cloud region centered in 

the IRT test section. Since perfect uniformity is practically not obtainable, for the 

purpose of the impingement tests, uniformity was accomplished when LWC variation 

within the region of interest was within ±15% of the average. 

Cloud uniformity was measured using two methods. In one method, a 6-ft by 6-ft 

stainless steel grid with horizontal and vertical increments 6 inches apart was used to 

determine cloud uniformity. The plane of the grid was normal to the flow and passed 

through the center of the turntable. Blotter squares, approximately 1.25 inches in size, 

were attached to this grid at 6 inch horizontal and vertical increments to cover the 

required 2-ft by 3-ft area (35 blotter strips were used during each cloud uniformity test). 

The tunnel was brought up to test speed and the blotters were sprayed. The dye 

distribution on each blotter was determined using the CCD reflectometer described in 

section 5 of this report. Next, the nozzles were adjusted to make the dye distribution and 

therefore the LWC more uniform. This grid/blotter method, which was laborious and time 

consuming, was similar to the one presented in Refs. 6 and 7. Figure 33 shows the 

uniformity grid (with/without blotter squares) installed in the IRT test section. 

 

NASA/TM—2002-211700 23
The second method for determining cloud uniformity was recently developed at 

NASA Glenn (Ref. 25). In this method, a 15-watt Argon-Ion laser beam was split into two 

beams, which were directed to sheet projectors or to a galvanometer using optic fibers. 

The light from the sheet projectors or the galvanometers was passed through large 

(64cm long) cylindrical lenses, which produced a laser sheet that spanned the tunnel 

width. By using only one or both of the cylindrical lenses, the height of the laser sheet 

could be adjusted to 2-ft or 4-ft respectively. The laser sheet was set approximately 

normal to the flow and was located a small distance upstream of the uniformity grid. The 

uniformity grid was left in the test section and was used for reference. The installation of 

the Argon-Ion laser beam system and its key components are shown in Figs. 34–36. 

The location of the 2-ft and 4-ft high laser sheet planes with respect to the IRT test 

section is shown in Fig. 37. 

A 14 bit CCD array camera was installed on the IRT spray bars between bars 

four and five and 21 inches to the left (looking upstream) of the vertical support beam as 

shown in Figs. 24 and 26. The camera was placed inside an airfoil fairing to minimize 

disturbance to the flow. Uniformity tests were conducted with all lights off in the test 

section and with the lights in the control room dimmed. With the tunnel set to the 

required airspeed (175 mph), the spray system was activated for approximately 30 to 50 

seconds. The intensity of the scattered laser light from the droplets crossing the laser 

sheet was recorded using the CCD camera installed on the IRT spray bars. High 

intensity regions in the recorded image corresponded to high LWC and vice versa. 

Using camera software, the image could be analyzed to determine variations in LWC 

within the desired uniformity region. Figure 38 shows example images of clouds 

obtained with the CCD camera. 

Extensive tests were conducted with the laser sheet method for all spray 

conditions selected for the impingement tests. The images obtained were used to adjust 

the locations of the nozzles until the desired LWC distribution was obtained. This 

method was found to be considerably more efficient than the grid/blotter method. In 

addition, the high resolution of the laser sheet technique proved valuable in 

understanding the effect of individual nozzles on the cloud LWC distribution. To verify 

the results obtained with the new uniformity method, a small number of tests were 

conducted with the grid and blotter strips. The results obtained showed good correlation 

with the laser sheet test results for all MVD conditions. 

4.7 MVD and LWC Measurements 

 Droplet size and distribution measurements for all spray conditions were 

determined using the NASA Glenn Forward Scattering Spectrometer Probe (FSSP) and 

the Optical Array Probe (OAP) shown in Figs. 39 and 40 respectively. Details regarding 

these probes can be found in Ref. 26. The LWC measurements were performed with the 

NASA Glenn hot wire King Probe Model KLWC-5 described in Ref. 27. Briefly, the King 

Probe operates on the theory that when a heated wire is maintained at a constant 

temperature, any excess power consumed by the wire is in proportion to the mass of 

water impacting on it. The installation of the King Probe in the IRT test section is shown 

in Fig. 41. 

NASA/TM—2002-211700 24
Two series of droplet and LWC measurements were conducted during each of 

the six-week IRT test entries in 1997 and 1999. One was conducted near the start of 

testing after the uniformity tests were completed and a second near the end of the 

impingement tests. Each series of droplet size, droplet distribution, and LWC tests 

consisted of several repeated measurements of the desired spray cloud conditions. 

MVD and LWC measurements were performed for all spray conditions used in the 

experiments. Short and long duration sprays were used in the LWC measurements to 

determine the effect of cloud unsteadiness on LWC. Traces of LWC as a function of time 

showed no significant impact of spray duration on the average LWC. Measured MVD 

and LWC distributions during the 1997 and 1999 IRT tests are summarized in Fig. 42a–

42c. MVD sizes and corresponding spray system air and water pressure settings are 

given in Tables 10a and 10b. Note that all data presented in Fig. 42 were obtained at the 

center of the IRT test section. 

Extensive tests were also conducted with the FSSP and King probes in 1997 and 

in 1999 to identify the impact of relative humidity on the cloud characteristics. These 

tests showed that the effect of relative humidity on LWC was considerable particularly 

for the 11-micron MVD case. Based on the relative humidity studies, it was decided to 

conduct all impingement tests at a relative humidity of 75% ± 5%. 

4.8 Reference Collector Mechanism 

Local LWC measurements were obtained with a device called the Reference 

Collector Mechanism (RCM) at all locations in the IRT test section corresponding to test 

model blotter strip locations. The purpose of these measurements was to correct the 

impingement data for local variations in LWC. The LWC measurements were performed 

with the reference collector mechanism described in Ref. 6. Due to test model 

installation, size, and angle of attack, blotter strips on each model tested resulted at 

different locations within the 2-ft high by 3-ft wide uniformity region established from the 

uniformity tests. By measuring the local LWC within the 2-ft by 3-ft test area, the effect of 

variation in cloud uniformity could be corrected, thus improving the accuracy and 

repeatability of the experimental impingement data. The RCM had six short blades and 

one long blade as shown in Fig. 43. Each blade was 0.2 inches wide and 1 inch in chord 

as shown in Fig. 44. The length (span) of the blades was 2 inches for the short blades 

and 9 inches for the long blade. 

The collector mechanism was placed in the empty IRT test section with its 

collector blades positioned as close as possible to the blotter strip locations on the test 

models. Since test model location varied depending on model installation and angle of 

attack, the collector mechanism had to be tested at several positions. For the collector 

tests, blotter strips 0.2 inches wide were placed on the collector blades so that the plane 

of each blotter strip was normal to the flow. The collector mechanism was tested at the 

same airspeed and cloud conditions as the test models. In addition, the spray duration 

for the collector tests was identical to that used for the airfoil tests Figure 45 shows the 

location of the collector blades with respect to the uniformity grid with the reference 

collector mechanism placed on the IRT turntable center. The locations of the reference 

NASA/TM—2002-211700 25
collector blades with respect to the blotter strip locations on the MS(1)-0317 airfoil at an 

angle of attack of zero degrees are shown in Fig. 46. 

The impingement data from the collector blotter strips were analyzed using the 

data reduction methods described in section 5 and the amount of dye in the freestream 

was determined at all locations of interest. The collector dye mass per unit area and its 

impingement efficiency were used to obtain the LWC in the freestream which was then 

used to convert the raw impingement data for each test model into impingement 

efficiency distributions. Table 11 provides computed impingement efficiency values for 

the collector blades for all test MVDs as well as the LWC measurements obtained with 

the King Probe during the 1997 and 1999 tests. Table 11 shows that the collector blades 

had high impingement collection efficiency. This is attributed to the small chord and 

thickness of the collector blades. 

4.9 Test Matrix 

Models and conditions for the 1997 (7/25/97 to 9/7/97) and 1999 (1/31/99 to 

3/1/99) IRT tests are provided in Table 12a and 12b respectively. All tests were 

conducted at a total air temperature of 48°F ± 8°F and a relative humidity of 75% ±5%. 

4.10 Surface Pressure Measurements 

Most of the models tested were equipped with surface pressure taps as 

discussed in section 4.2. Surface pressures for each model were obtained prior to the 

impingement tests. Pressure measurements were performed with the IRT electronically 

scanned pressure (ESP) system. Six 32-port (±5 psid) ESP modules were available in 

the IRT, providing a total of 192 pressure channels. One port in each module was used 

for a check pressure; thus 31 channels per module were available for test data, or a total 

of 186 ports. The ESP system applied a three-point pressure calibration to all port 

transducers. The calibration pressures were measured with precision digital quartz 

transducers. This on-line three-point calibration ensured that measurement errors were 

not greater than ±0.1% of full-scale. The standard calibration interval was every 400 

cycles (approximately 15 minutes). The experimental pressure data were used to 

validate the computed pressure distributions prior to performing the impingement 

analyses. 

4.11 Impingement Test Procedure 

To obtain water droplet impingement data for a test model the following steps 

were performed. 

1. The spray system air and dyed water pressures were set to produce the required 

MVD. Pressure settings for all MVD sizes used in the impingement tests are 

given in Tables 10a and 10b for the 1997 and 1999 tests respectively. 

2. Blotter strips were attached at the required locations on the forward part of the 

test model with aluminum tape. The blotter strips were approximately 1.5 inches 

wide and had various lengths, depending on model geometry, angle of attack 

and MVD size. For the majority of the models the blotter strips were rectangular 

in shape. For the swept NACA 64A008, 25%-scale BJE, and full-scale business 

NASA/TM—2002-211700 26
jet tail section, however, V-shape blotter strips were used so that the blotter strip 

was in the streamwise direction. Each blotter strip was marked on its backside 

with the run number, test model and location on the model. 

3. The tunnel airspeed and in the case of the S-duct the inlet mass flow was set to 

the required value, the spray system was activated for a short period of time and 

a dye deposit was obtained on the blotter strips. The spray time duration varied 

from approximately 2 to 18 seconds depending on MVD size as shown in 

Table 10. 

4. The tunnel airspeed was reduced to idle, the blotter strips were carefully 

removed from the model and were placed in the control room to dry prior to 

being stored. The model was wiped clean and new blotter strips were placed on 

the model for the next test. 

Each test condition was repeated three to four times (i.e., 3 to 4 tests per 

condition) to establish a measure of test repeatability. In some cases as many as 10 

repeats were performed over a period of two days to better determine the repeatability 

of the experimental technique. 

Periodically, the collector mechanism was tested between model tests to provide 

the required local LWC measurements for reducing the model impingement results. 

5.0 Data Reduction Method 

Two methods have been developed over the years for reducing impingement 

data. The first method was developed by NACA in the 1950’s and was based on 

colorimetric analysis (Ref. 1). The second method was developed by WSU/Boeing in the 

1980’s and was based on diffuse reflectance spectroscopy (Refs. 6, 28 and 29). This 

method was significantly more efficient than colorimetric analysis and provided higher 

resolution impingement data. In an effort to further increase the efficiency of the data 

reduction process to the point where the data could be reduced on-line, a new 

implementation of the diffuse reflectance spectroscopy method was developed during 

the course of this research program. Details of the data reduction methods and the 

semi-automated systems developed for extracting and analyzing the data from the 

blotter strips are presented below. 

5.1 Reflectance Spectroscopy 

The data reduction methods used in this work rely on the assumption that when a 

dye-laden blotter strip is illuminated by a light source the intensity of light scattered by 

the dyed paper is a measure of the dye mass per unit area of the paper. Regions on the 

blotter strip corresponding to high impingement rates are darker in color and reflect less 

light than those corresponding to low impingement rates. Regions with no dye 

accumulation are white and scatter the maximum amount of light. The relation between 

dye concentration and reflectance is not linear and is defined from calibration tests. To 

enhance the sensitivity of the reflectance method, the dye must have a strong 

absorption at the wavelength of the light source used for illuminating the blotter strips. 

NASA/TM—2002-211700 27
For improved accuracy, dye penetration normal to the blotter surface should be kept to a 

minimum since the data reduction method relies on surface reflectance measurements. 

The acceptable level of dye penetration depends on the data reduction system and is 

determined from experiments. 

5.2 Reflectance Calibration Curves 

The reflectance calibration curve relates normalized reflectance from the dyeladen blotter strip to dye mass and therefore water impingement on the blotter strip. The 

curve is a standard against which the reflectance of each blotter strip is compared 

during the data reduction process. 

To produce the reflectance calibration curve, approximately 30 rectangular blotter 

samples each 1.5-inch wide by 15-inch long were prepared over the course of this 

research program. Each blotter sample was sprayed with blue dye solution until a 

uniform blue color density was obtained over the whole rectangular blotter sample. By 

varying the spraying time and the concentration of the dye solution, blotters with a wide 

range of uniform color densities were obtained covering the spectrum from very light 

blue to dark blue color. Next, three circular disks each 1.13-inch in diameter were 

punched out from each of the rectangular blotter samples. The average reflectance of 

each of the discs was measured using both the laser and CCD reflectometers described 

below. The dye mass from each disc was extracted by the WSU chemistry lab using the 

method of colorimetric analysis described in Ref. 6. Next, the dye mass from each 

blotter disc was divided by the disc area to provide the dye mass per unit area. The 

normalized reflectance calibration curves shown in Figs. 47-50 were produced by 

plotting the normalized reflectance from each disc sample against the corresponding 

dye mass per unit area. In these curves, a normalized reflectance value of 1 

corresponds to the white blotter paper and indicates zero dye mass. More than 70 dyeladen blotter discs were used to define the laser and CCD calibration curves shown in 

figures 47–50. 

5.3 Data Reduction Systems 

Two systems were used to reduce the raw impingement data obtained during the 

1997 and 1999 impingement tests. The first system was a laser reflectometer, which 

was developed and tested extensively during the 1985 and 1993 research programs 

conducted by WSU and Boeing Company. The second system made use of a CCD 

array camera for digitizing the images of the dyed blotter strips, which were then stored 

for later analysis. 

A prototype CCD data reduction system was developed in 1992 at Wichita State 

University. This system consisted of an 8-bit Cohu 4080 CCD camera with a Dipex 

frame grabber connected to a personal computer. Tests showed that this system was 

capable of extracting impingement data from dyed blotter strips. However, it was 

determined that a system with a resolution higher than 8-bits was required to accurately 

resolve the variation in blue color density, particularly near the region of maximum 

impingement. Further development of the method was hindered by the cost of highresolution cameras at that time. 

NASA/TM—2002-211700 28
In 1995, Bragg et al. (Ref. 30) developed a method based on a 14-bit CCD 

camera array which was used to analyze impingement data from tests conducted with a 

NACA 652-015 airfoil. Good correlation with other published experimental data for this 

airfoil was demonstrated. 

The main advantages of a CCD data reduction system are speed and spatial 

resolution. Such a system has the capability of providing on-line data reduction during 

impingement testing. 

The Laser and CCD data reduction systems used in this work are described 

below. 

5.3.1 Laser Reflectometer

The main components of the laser reflectometer are depicted in Fig. 51a and 

include: (a) a red He-Ne laser with a wavelength of 632.8 nm, (b) a rotating drum for 

mounting the blotter strips, (c) a convergent lens for focusing the reflected light from the 

blotter strip onto a silicon photodetector and (d) a EG&G silicon photodetector for 

converting the reflected light collected by the lens into a voltage (V1) which is stored for 

further analysis, and (e) a splitter glass plate and another silicon photodetector for 

monitoring fluctuations in laser light intensity. The voltage (V2) from the second 

photodetector is also stored and is used in the data analysis. Details of the laser 

reflectometer can be found in Ref. 6. 

A PC based digital data acquisition system was developed to control the 

operation of the reflectometer and to analyze and plot the impingement data. Note that 

the maximum absorption of the blue dye selected for the impingement tests occurred at 

629.5 nm, which is very close to the wavelength of the laser, thus, ensuring that small 

changes in dye color density could be resolved by the system. 

The process of converting the raw color density distribution from a dye-laden 

blotter strip into impingement efficiency distribution involved a number of steps. First, the 

raw reflectance versus surface distance data (see Fig. 51b) were extracted by mounting 

each blotter strip on the drum of the laser reflectometer and scanning the strip along its 

length as shown in Fig. 52a and 52c. The voltages V1 and V2 from the two 

photodetectors obtained during a scan were stored on disk and were used to generate 

the raw reflectance values shown in Fig. 51b. Note that V-shape strips and long 

rectangular blotter strips had to be scanned in segments because the reflectometer 

could only accommodate rectangular strips with a maximum length of 16.5 inches. The 

raw reflectance data from each segment of the blotter were then combined using a 

computer program and were stored for further analysis. The spatial resolution of the 

reflectometer was 47 data points per inch. To convert the raw reflectance values into 

impingement distributions a FORTRAN program developed during the course of this 

research was used. The steps involved in generating the final impingement distribution 

curves are outlined below: 

NASA/TM—2002-211700 29
1. The raw reflectance values stored in electronic format during the data extraction 

process were divided by the reflectivity of the bare (white) blotter paper to obtain 

normalized reflectance data using the equation below. 

( )

( )White blotter paper

Dyedblotter paper 

Raw reflectance of white blotter paper

Raw reflectance of dyedblotter paper

1 2

1 2

n

V V

V V

R

=

=

 (5.1) 

The raw reflectance of the white blotter paper was determined by scanning 

several sample white strips to obtain an average value. This value was verified at 

the beginning and end of each data reduction session. 

2. The normalized reflectance data were converted into dye mass per unit area 

using the laser calibration curves in Figs. 47 and 48. 

3. The impingement efficiency for each data point recorded was obtained from the 

following equation. 

β = × βCollector Average Collector Dye Mass per Unit Area

LocalDye Mass per Unit Area (5.2) 

Collector strips were reduced prior to the model strips since the collector dye 

mass was required to define the impingement efficiency of each test model. The 

value of βCollector is a function of MVD and is given in Table 11. 

5.3.2 Charge-Coupled Device (CCD) Reflectometer

A schematic diagram of the CCD system developed by WSU is given in Fig. 53a. 

The system consisted of a Pentium 200 MHz PC, a CCD array camera with 14-bit 

resolution, a camera electronics unit, a camera PC controller, a 24 mm Nikkor lens, four 

(4) Quartz halogen lamps with precision beam control, four 629nm band pass filters one 

for each lamp, two power supplies for the lamps, a camera stand, a 1.5-ft wide by 2.5-ft 

long non-reflecting glass sheet, and a portable dark room for reducing the data. 

The data from each dye-laden blotter strip were extracted as follows. Each strip 

was placed on the table inside the dark room next to a reference scale. The highlight 

mark on the blotter strip was aligned with a fixed mark on the reference scale. The nonreflecting glass was placed on top of the blotter to keep the blotter flat on the table. The 

halogen lights were set to the required intensity level by adjusting the voltage and 

amperage of the two power supplies. Light from each lamp was passed through a 600 

nm ±40 nm filter to enhance light absorption by the blue dye on the strip. The camera 

shutter was activated through the PMIS software and it was kept open for a specified 

time period, which was determined during the system calibration. A 512 by 512 pixel 

array image of the blotter strip was obtained and it was stored on disk for later analysis. 

The camera was capable of resolving nearly 14 bits (or approximately 16000) of 

intensity values of scattered light from the blotter strip. The blue strip was removed and 

a white reference strip was placed on the table in exactly the same location. The 

NASA/TM—2002-211700 30
process was repeated and a 512 by 512 image of the white strip was obtained and 

stored. The raw reflectance from the white strip was used to normalize the raw 

reflectance from the dyed strip. Figure 53b shows a typical raw intensity plot obtained 

from PMIS software for a tested blotter strip. Note that, the lower intensity values on the 

plot correspond to the darker (dyed) region on the blotter strip. 

Windows driven software, written in PV-WAVE command language and in 

Microsoft FORTRAN, were developed for the CCD data reduction system to process the 

images from the dyed strips into impingement distributions. The process for generating 

the impingement efficiency distributions involved the following steps: 

1. Each dyed strip image and the corresponding white strip image were read using 

the PV-WAVE software developed. Both images were corrected using the bias, 

dark, flatfield and reference images, which were obtained and stored during the 

calibration of the CCD array camera. 

2. Using the computer mouse, a rectangular region was selected on the white strip 

image. This region was processed by the software to provide an average intensity 

value for the white paper. 

3. For a rectangular dye-laden blotter strip, a region that was large enough to cover 

the complete extent of dye impingement was selected using the computer mouse 

as shown in Fig. 52b. The location of the highlight point on the strip (typically the 

point on the leading edge of the test geometry corresponding to x/c=0) and a 

length scale were defined for determining surface distance along the strip. For a 

V-shape strip, four points were selected by the user as shown in Fig. 52d to 

define the extent of impingement. 

4. The software produced an array of dye intensity versus surface distance for the 

dyed strip. These values were normalized by the average white blotter paper 

intensity value to produce an array of normalized intensity (i.e., 0 to 1) distribution 

versus surface distance, which was stored for further analysis. 

Because impingement tests were repeated a number of times for each test 

condition, several blotter strips were produced for each condition tested. A FORTRAN 

program was developed to process the normalized intensity values from several blotter 

strips into a single array of averaged normalized intensity versus surface distance. This 

array was converted into dye mass (μg/cm2) versus surface distance using the 

calibration curve shown in Fig. 49 and 50. Next the local impingement efficiency values 

were obtained from Eq. 5.2, which is identical to the one used for processing the data 

from the laser reflectometer. 

NASA/TM—2002-211700 31
6.0 Analysis Methods 

 Analytical results for the two-dimensional test cases involving the MS(1)-0317, 

NACA 652-415, commerical transport tail section, GLC 305 and NLF(1)-0414 airfoils 

were obtained with the LEWICE-2D code version 1.6. This code is a panel-based ice 

accretion prediction code that applies a time-stepping procedure to calculate the shape 

of an ice accretion. The potential flow field is calculated in LEWICE 1.6 (Ref. 31) using 

the Douglas Hess-Smith 2-D panel code. This potential flow field is then used to 

calculated the trajectories of particles and the impingement points on the body. Note that 

the impingement analysis for the three-element high lift system was obtained with 

theLEWICE3D code and a 2-D incompressible Navier-Stoke based flow solver (INS2D). 

 Three-dimensional analysis for NACA 64A008 finite swept wing, 25%-scale 

business jet empennage, full-scale business jet horizontal tail, and s-duct engine was 

performed on a single processor (R12000) of an SGI Octane computer. The following 

steps were required to complete the impingement analysis for the three-dimensional 

configurations. 

1. The grid for the trajectory calculations was constructed using the ICEGRID code 

2. The PMARC code was used to generate the velocities on this grid and to generate 

the surface velocities needed in the LEWICE-3D code. 

3. The impingement analysis was performed with the LEWICE-3D code using the panel 

model and the surface velocity information obtained in step 2 above. 

6.1 Grid Generation - ICEGRID

 TheICEGRID program was developed at Glenn Research Center by Bidwell and 

Coirier specifically for the task of optimizing trajectory calculations in the LEWICE-3D 

code for the panel code interface. ICEGRID automatically produces grids which are 

optimal for trajectory calculations. An optimal grid for trajectory calculation should have a 

minimum number of cells, allow for quick traversal (for velocity interpolation), and have 

clustering of cells near regions of impingement. The tri-binary, multi-block grid structure 

coupled with a feature that generates refinement only external to the surface of the 

geometry results in a program that generates grids with a minimum number of cells and 

which are quickly traversed. The use of refinement regions and functions within the 

program allows the user to easily control cell size and density in any region of the grid. 

The ICEGRID program also produces a minimum of grid points which reduces the panel 

code calculation times. The program requires the surface geometry and an input file 

describing the grid volume and refinement parameters. The code refines the grid near 

regions of interest which can include the geometry, parts of the geometry, and lines or 

points input by the user. The code is similar to an oct-tree method (Ref. 32) in that it 

recursively divides the original grid volume until the refinement criteria for each cell have 

been met. The code will not refine cells internal to the geometry. ICEGRID is different 

from most oct-tree methods in that the grid volume is allowed to be multiply skewed, 

multiblock and different refinement functions can be used in any direction. This last 

feature is where the code really differs from the oct-tree methods in that it allows a given 

cell to be divided into 8, 4 or 2 cells depending on the refinement function instead of the 

NASA/TM—2002-211700 32
oct-tree method which divides a cell into 8 cells if the refinement is required. This results 

in grids with much fewer cells for cases where gridding requirements are disparate in the 

different directions (e.g. swept wings which have a much smaller cell size requirement in 

the chordwise direction than in the spanwise direction). The grids used in the 

impingement analysis of the swept tail models are shown in Figs. 54–56. The grids were 

all swept to align with the leading edge of each model and were only generated for one 

side of the symmetry plane. 

 Cell size is critical in producing accurate droplet trajectories. The panel and grid 

cell size must be similar and small enough to resolve the velocity gradients in the vicinity 

of the wing. Specific grid properties for each swept tail model are summarized below: 

Geometry No of Grid 

Points 

Min Chordwise/surface 

normal grid spacing 

Min Grid Cell 

Size - Spanwise 

Max Cell Size 

for grid 

NACA 64A008 216,708 0.159 cm 5.08 cm 40.64 cm 

Full-Scale BJ 

Tail 

259,066 0.159 cm 5.08 cm 40.64 cm 

25%-scale BJ 

Tail 

224,582 0.04 cm 1.27 cm 10.16 cm 

 The grid plane at y = 0 shows the major features of the grid. It took approximately one 

hour of CPU time to generate each of the grids. 

6.2 Flow Solver - PMARC 

 PMARC is a first order 3D potential flow panel code (Ref. 33). Geometries are 

represented with quadrilateral surface panels which have constant doublet and source 

distribution. The formulation used in PMARC results in a solution that is second order 

accurate allowing for accurate flow solutions with fewer panels and less CPU time than 

other first order methods. The disadvantage of this method is that because a numerical 

differentiation is used to generate the velocity distribution careful panelling is required to 

prevent numerical errors. The code can generate solutions for internal and external 

compressible flows and can handle a large number of panels (approximately 10,000). 

 For the current study, PMARC computations were performed using a steady, 

isolated flow with a y = 0 plane of symmetry as shown in Figs. 54c, 55c and 56c. The 

swept 64A008 panel model contained 2303 panels, the full-scale business jet tail section 

panel model contained 2162 panels and the 25%-scale business jet empennage panel 

model contained 2162 panels. Flow solutions were calculated for two angles-of-attack 

(0°, 6.25° for the NACA 64A008 model; 1°, 6° for the full-scale business jet tail section 

and 2°, 7° for the 25%-scale business jet empennage model. In cases where surface 

pressure information was available (i.e. the swept NACA 64A008 model and the 25%-

scale business jet empennage model) an attempt to match the analytical and 

experimental pressure distributions was made by varying the analytical angle-of-attack. 

In these cases, the analytical and experimental angles-of-attack were different. Matching 

the pressure distributions ensured that the experimental and analytical flow models had 

NASA/TM—2002-211700 33
similar flow fields which is the key in the consistency of the collection efficiency 

comparisons (Ref. 34). The flow solutions and velocity calculations took approximately 

150 minutes for each of the cases. 

6.3 Impingement Analysis - LEWICE-3D 

 The LEWICE-3D grid based code incorporates trajectory, heat transfer and ice 

shape calculation into a single computer program. This code can handle generic 

multiblock structured grid based flow solutions, unstructured grid based flow solutions, 

simple cartesian grids with surface patches, and adaptive grids with surface patches. 

The latter two methods allow the use of generic panel code input which is a 

computationally efficient method for generating ice shapes. The code can handle 

overlapping and internal grids and can handle multiple planes of symmetry. Calculations 

of arbitrary streamlines and trajectories are possible. The code has the capability to 

calculate tangent trajectories and impingement efficiencies for single droplets or droplet 

distributions. Ice accretions can be calculated at arbitrary regions of interest in either a 

surface normal or tangent trajectory direction. The LEWICE-3D code has been used in 

previous calculations for isolated wings, inlets, ducts, and full aircraft configurations 

(Refs. 35–41). 

 The methodology used in the LEWICE-3D analysis is desribed in Ref. 42. In 

general, the trajectory analysis requires six basic steps for each section of interest at 

each time step as follows: 

1. In the first step the flow field is generated by the user. 

2. Surface streamlines are calculated during the second step. The surface streamline 

analysis uses a variable step size fourth-order Runge-Kutta integration scheme 

developed by Bidwell (Ref. 40). 

3. In the third step, tangent trajectories are calculated at the region of interest. 

4. In step 4, an array of particles is released between the tangent trajectories. These 

impacting particles are used to calculate collection efficiency as a function of surface 

position. The trajectory analysis is basically that of Hillyer Norment (Ref. 43) with 

modifications by Bidwell. At the heart of the trajectory analysis is the variable step 

predictor-corrector integration scheme developed by Krogh (Ref. 44). 

5. Step 5 involves interpolating or extrapolating the collection efficiencies onto the 

streamlines. 

 LEWICE-3D calculation times varied for the different cases depending upon the 

drop size and the number of trajectories. The LEWICE-3D calculation times are heavily 

dependent upon grid size and structure because the largest portion of the LEWICE-3D 

calculation time (greater than 99%) is spent calculating velocities at specified points, 

which involves searching through the grid tree structure for the cell in which the point is 

located. The trajectory integration time for the cases varied from 0.02–0.05 seconds. 

Approximately 100 trajectories were required for each drop size at each section of 

interest for the droplet impingement calculations. This resulted in calculation times of 

approximately 250–500 seconds for each of the tail cases (2 sections-of-interest, 27 bin 

distribution). 

NASA/TM—2002-211700 34
 The S-duct engine inlet analysis was comprised of two tasks. The grids and flow 

solutions using the NPARC flow solver were provided by the engine manufacturer. 

NASA Glenn generated the trajectory analysis using the LEWICE-3D program. 

 There were six blocks of grid systems with a total of 997,450 grid points as shown 

in Fig. 57. A multi-block Navier-Stokes flow solver (NPARC) was used to obtain the 

internal flow solution for a Reynolds number of 591,290 based on a reference length of 

approximately 16 inches (see Fig. 22f) and a Mach nubmer of 0.22. 

 The trajectory analysis was conducted with the LEWICE-3D program with an 

eight-bin distribution representing the IRT cloud for each of the three droplet sizes used 

in the experimental investigation. The Monte-Carlo collection efficiency method was 

used to generate the collection efficiencies on the inlet outer and inner surfaces. Each 

bin of the distribution required about 1,000,000 droplet trajectory calculations and took 

about 240 hours on a single 300 MHz SGI Octane processor to complete. 

7.0 Results and Discussion 

In this section, the accuracy of the experimental and data reduction methods is 

discussed and sources of error are identified. Results from studies performed during the 

experimental investigation are used to quantify the effect of test variables on test 

repeatability. Experimental impingement data for all models tested are presented and 

are compared with analysis data obtained with the LEWICE-2D and LEWICE-3D 

computer codes discussed in section 6. All the experimental data are averaged data 

from repeated tests. Geometric, flow and droplet parameters for the airfoil and finite 

wing models used during the impingement tests are summarized in Table 13. 

7.1 Repeatability of Experimental Method 

Test repeatability is an important indicator of the quality of the experimental 

method. Repeatability is defined as the maximum percent difference of repeated test 

runs from the average. Typically, the maximum difference is observed at the point of 

maximum impingement efficiency. Previous experimental investigations (Refs. 1–7 and 

30) have demonstrated test repeatability in the range of 10%–30%. The main 

contributor to this uncertainty has been the experimental method and in particular, the 

repeatability of the spray clouds. 

An uncertainty analysis presented in Ref. 30 showed that errors in spray time, 

dye concentration, spray system pressures, tunnel velocity and cloud unsteadiness due 

to spray bar-induced turbulence alone were responsible for 14% variation in βmax. Tests 

performed during the present investigation have identified and quantified the uncertainty 

of important experimental variables and their effect on test repeatability. In general, the 

results obtained support the findings in Ref. 30 with one significant exception: relative 

humidity was found to be critical to test repeatability. 

NASA/TM—2002-211700 35
7.1.1 Spray System Performance and Repeatability 

The spray system is an important component of the experimental method and is 

directly responsible for the repeatability of the spray cloud. Important spray system 

variables include air and water pressures, spray duration, and nozzle performance. In 

addition, since spray system pressures are set based on information gathered from 

pressure transducers distributed throughout the system, the accuracy of these devices 

is critical to spray system performance. The accuracy of the pressure transducers used 

in this work is presented in Table 9. 

Experimental results presented in Table 10 and Figs. 58 and 59 indicate that the 

twelve-nozzle spray system was capable of maintaining water and air pressures to 

within ± 1 psi. A detailed error analysis was performed using the calibration equations 

for the MOD-1 nozzles provided by NASA (Refs. 45 and 46). This analysis showed that 

variations of ±1 psi in spray system pressures would result in ±0.5 microns error for the 

11.5-micron MVD and ± 1 micron error for the 21-micron MVD. These results are 

supported by repeated FSSP and OAP measurements presented in Fig. 42. 

Computations performed with LEWICE-2D (Ref. 31) showed that the errors in βmax due 

to ±0.5 microns, and ±1 micron error in MVD were of the order of ±1% (i.e., ∆β = .01) for 

the 11.5-micron and 21-micron cases as demonstrated in Fig. 60a. The effect of the 

MVD uncertainty on the impingement limits can be estimated from Fig. 60b. All 

computations were performed with monodispersed (i.e., single drop size) droplet 

distributions. 

 The NASA Glenn MOD-1 nozzles used in this investigation have a very thin water 

tube with a diameter of 0.0155 inches (0.4 mm). A bent or clogged water tube can 

cause significant changes in cloud uniformity. It is very difficult to estimate the error due 

to nozzle characteristics. The approach taken in this work was to carefully select and 

check all nozzles used in the 12-nozzle spray system. The first step was to select 

nozzles with very similar flow coefficients (Cf

). The flow coefficient of a nozzle is defined 

as 

P

W Cf ∆

 =

Where, W is the water flow rate in gallons per minute and ∆P is the differential pressure 

between the water and air supplied to the nozzle in psi. The flow coefficients of the 12 

nozzles selected varied from 0.00398 to 0.00406 as shown in Figs. 25 and 27. Next, 

each MOD-1 nozzle was visually inspected to verify that its water tube was aligned with 

the nozzle axis. To help prevent nozzle clogging, the water solution from the tank was 

filtered prior to entering the MOD-1 nozzle assemblies. Since filtering does not eliminate 

the problem of nozzle clogging, a very sensitive flow meter was installed in the spray 

system. During each test, the flow rate from all 12 nozzles was monitored. Tests 

performed with partially clogged nozzles showed that the flow meter could easily detect 

changes in the total flow rate even with a single nozzle partially clogged. Flow rates 

corresponding to each test MVD case are presented in Table 10. Figure 61 shows the 

NASA/TM—2002-211700 36
variation in the 12-nozzle water flow rate for selected tests conducted during the 1999 

IRT entry. As an added precaution, a video camera was installed near the entrance of 

the test section to monitor the nozzles during each test. Finally, each time the spray 

system pressures were adjusted to change the MVD size, two to three spray tests were 

performed to verify that all nozzles were spraying consistently. 

Repeatability of spray duration is important to the accuracy of the experimental 

results. Spray duration was controlled by the PC timer unit, which was accurate and 

repeatable. However, another factor, which affects spray duration and cannot be 

controlled easily, is nozzle on/off performance. This is related to the MOD-1 nozzle 

design and solenoid on/off response. During the evaluation of the spray system, each 

nozzle was videotaped from the start to the end of a spray test. By counting video 

frames (30 frames per second), it was determined that the spray required approximately 

0.06 seconds to reach full strength after activation of the solenoid valves. Upon deactivation of the solenoid valves, however, the spray “shut off” time varied from 0.2 to 

0.4 seconds depending on nozzle. In summary, the variation in spray duration was 

approximately 0.2 seconds between tests. Since spray duration was set according to 

MVD size, the variation in spray duration for the 1997 impingement tests was 1% for the 

18 seconds spray (MVD = 11.5μm), 3% for the 6 seconds spray (MVD = 21μm), and 7% 

for the 3 seconds spray (MVD = 92μm). Shorter sprays were selected for the larger 

MVDs to avoid blotter paper penetration by the dye solution. Note that during the 1999 

IRT tests, spray times were reduced as shown in Table 10b. This was done to enhance 

the sensitivity of the data reduction method by further limiting dye penetration into the 

blotter paper. For the new spray times selected the variation in spray duration was 2% 

for the 9 seconds spray (MVD = 11 μm), 4.7% for the 3.8 seconds spray (MVD = 21μm), 

9.5% for the 2.2 seconds spray (MVD = 94μm). 

Figures 62 and 63 show typical spray system air and water pressure histories for 

each of the three MVD cases used in the 1997 and 1999 impingement tests 

respectively. A small transient period, approximately 0.5 to 1 seconds in duration is 

observed in the pressure traces for some of the test cases. This transient behavior was 

also observed during the MVD and LWC measurements with the FSSP, OAP and KING 

probes. Basically, the cloud MVD and LWC stabilized to their final values within 0.5 to 1 

seconds. 

7.1.2 Cloud Uniformity

Cloud uniformity and in particular LWC uniformity, is the most challenging aspect 

of the experimental method and contributes significantly to the experimental uncertainty. 

During the course of the 1997 and 1999 impingement tests, extensive cloud uniformity 

tests were performed using the laser sheet as well as the grid and blotter method. The 

objective of the uniformity tests was to adjust the WSU spray nozzle locations in order to 

produce spray clouds with uniform LWC over a 2-ft high by 3-ft wide area at the center 

of the IRT test section. This area was determined to be sufficient for testing the wind 

tunnel models selected for the impingement tests. Figures 64–66 show typical cloud 

uniformity results in terms of normalized reflectance for the 11, 21, and 94-micron MVD 

cases obtained with the grid and blotter method during the 1999 IRT entry. Note that 

NASA/TM—2002-211700 37
the sharp reflectance spikes in these figures (normalized reflectance values close to 1.0) 

correspond to the grid bars which were spaced 6 inches apart in both the horizontal and 

vertical directions. The results presented show that in most cases the cloud uniformity 

was in the range of ±10% to ±15% from the average within the area of interest. 

However, in spite of the extensive efforts made to obtain a spray cloud with 

uniform LWC, local variations within the test area are usually present and these 

variations could significantly affect the quality of the experimental data. These local 

variations are the result of the large number of variables that influence the spray cloud 

characteristics. Parameters such as nozzle performance, spray system settings, model 

geometry, angle of attack, relative humidity, tunnel turbulence level, etc. could affect the 

LWC distribution in the wind tunnel test section. Furthermore, the interaction between 

these variables was not easy to assess. For example, high spray system air pressures 

required for certain cloud conditions could increase the level of turbulence in the tunnel 

and the level of cloud unsteadiness. This is why it is so important that local LWC 

measurements are made at exactly the same locations as the model strips. Typical 

local LWC measurements performed with the collector mechanism are presented in 

Figs. 67a and 67b in terms of normalized reflectance. Variation in normalized 

reflectance was between –2.8% and +1.4% from the average and corresponded to a 

dye mass density (i.e., LWC) variation from +9% to –4% respectively. Thus, although 

the variation in LWC within the 2-ft by 3-ft area of interest was ±10% to ±15%, local 

LWC measurements exhibited less variation. 

However, measurement of local LWC does not eliminate the effect of cloud nonuniformity. This is because the collector mechanism and the model are not subjected to 

exactly the same flow field. The presence of a lifting wing modifies the flow field, 

particularly in high lift situations. Thus, although blotter strips on the wing and collector 

could be placed so that they corresponded to the same physical location in the test 

section, the dye impinging on model and collector strips could originate from spatial 

locations in the cloud with different values of LWC. 

7.1.3 Relative Humidity

 The effect of relative humidity on the experimental impingement data was partially 

investigated by the WSU/Boeing team during the 1985 and 1989 impingement tests at 

NASA Glenn. However, attempts to quantify the effect of relative humidity were not 

successful. Recently, experiments conducted by Bragg et al. (Ref. 30) showed that 

relative humidity did not have a significant effect on spray clouds produced with three 

NASA Glenn STANDARD nozzles. This conclusion was drawn from cloud droplet 

distribution measurements for five humidity levels varying from 10% to 63%. 

 During the present investigation, extensive tests were performed to quantify the 

effect of relative humidity on cloud droplet distribution and LWC, since these parameters 

are directly related to the repeatability of the experimental impingement data. Droplet 

distributions and LWC measurements were conducted for relative humidity levels 

ranging from 55% to 95%. Droplet measurements were obtained with the NASA Glenn 

NASA/TM—2002-211700 38
FSSP probe while LWC measurements were performed with the NASA Glenn KING 

probe. Results from this study are presented in Table 14, and in Figs. 68a and 68b. 

Table 14 shows that relative humidity had a significant effect on droplet count and 

LWC but not on cloud MVD. The effect of relative humidity on cloud LWC for MVDs of 

11, 11.5, 21, 92 and 94 microns is demonstrated Figs. 68a and 68b. For the 1997 IRT 

tests and for the 11.5μm MVD, increasing the relative humidity from 60% to 90% 

increased LWC from 0.01 to 0.12 g/m3. Thus, a 30% increase in relative humidity 

increased the local LWC by a factor of 12. Similar tests conducted during the 1999 IRT 

tests showed that a 30% increase in relative humidity resulted in a threefold increase in 

cloud LWC. Relative humidity had a smaller but still significant effect on the LWC for 

clouds with larger MVDs. For instance, tests conducted during the 1997 IRT entry 

showed that for the 21μm cloud, a 30% increase in relative humidity increased LWC 

from 0.12 to 0.21 g/m3 while for the 92μm case, the same increase in humidity increased 

LWC from 0.18 to 0.28 g/m3

. 

 The results of the relative humidity study demonstrate that changes in relative 

humidity of the order of ±10% could result in large variations in the impingement results 

and that the repeatability of the data can be adversely affected by changes in relative 

humidity. In particular, if the collector and the models are tested at different relative 

humidity levels, the experimental error can be considerable. It should be noted that the 

NASA Glenn MOD-1 nozzles used in the 1997 and 1999 impingement tests have lower 

flow rates (approximately 1/3 lower) than the STANDARD nozzles. Therefore, spray 

clouds produced with the MOD-1 nozzles could be more sensitive to changes in relative 

humidity. 

7.1.4 Dye Recirculation

 Dye recirculation could adversely affect the experimental impingement results. 

Several tests were conducted to investigate the possibility of dye recirculation in the 

tunnel. Initially, blotter strips were attached on the IRT spray bars near the tunnel 

centerline so that the blotters were facing upstream. After two days of testing, the blotter 

strips were scanned with the CCD reflectometer. No dye trace was found. Five weeks 

after the start of the impingement tests, the tunnel turning vanes upstream and 

downstream of the refrigeration section, which was located just upstream of the IRT 

spray bars, were examined for dye deposits. Several turning vanes were wiped with a 

clean wet cloth to determine if dye deposits were present. Small traces of dye were 

found in the vanes upstream of the refrigeration section. However, no dye trace was 

found downstream of the refrigeration section. To investigate the possibility of dry dye 

powder recirculation in the tunnel, several wet blotter strips and a wet cloth were 

attached to the IRT spray bars facing upstream. The blotters and cloth were moistened 

periodically to make sure that they remained wet between impingement tests. After two 

days of testing, the blotters and cloth were examined for dye deposits. No visible dye 

traces were observed. Thus, it is concluded that dye recirculation was not a problem in 

the present investigation. 

NASA/TM—2002-211700 39
7.2 Repeatability of Data Reduction Methods 

A discussion on accuracy and repeatability of the data reduction methods is 

presented in this section. Key factors affecting the data reduction method include: blotter 

paper consistency, calibration curve relating normalized reflectance to dye mass, depth 

of dye penetration into the blotter, uniformity of blotter strip illumination and performance 

of hardware components. 

7.2.1 Blotter Paper Characteristics

It is advisable to select a thin blotter paper for the impingement tests since a thin 

paper conforms better to the surface of the test model and minimizes aerodynamic 

interference. The paper should also retain its texture throughout the testing and it should 

be chemically inert to the dye and water. Its composition should minimize dye diffusion 

in the lateral direction. Furthermore, the paper should be mechanically strong to 

withstand the aerodynamic forces experienced during testing. 

Three types of white blotter paper were evaluated for the impingement tests: a 

James River Paper Company 100# Verigood blotting paper (VG100#) with a thickness 

of 0.53 mm, a James River 80# Verigood blotting paper (VG80#) with a thickness of 

0.45 mm, and a Whatman WH3MM Chromatography paper (W3MM) with a thickness of 

0.35 mm. To determine the consistency in the reflectance properties of these papers, a 

large sample of blotter strips were scanned with both data reduction systems. The 

results obtained showed that the VG100# and W3MM papers exhibited ±2% variation in 

raw reflectance from the average. Reflectance variation for the VG80# was in the range 

of ±3% to ±4%. It should be noted that some of the variation observed was due to the 

data reduction systems. 

Several dye-laden blotter paper samples were produced with all three types of 

blotter paper to define the normalized reflectance versus dye mass calibration relation 

for each paper. The data for the laser reflectometer are presented in Fig. 69. 

Corresponding data for the CCD data reduction system are depicted in Fig. 70. Note 

that these are not the final calibration data for the data reduction systems. They are 

presented here to demonstrate the effect of paper characteristics on the calibration 

curve and on the data reduction process. 

The reflectance versus dye mass relation exhibited a steep decline in normalized 

reflectance for low dye mass densities followed by a more gradual decline. As the dye 

mass density increased beyond a certain value, the slope decreased significantly and in 

some cases it was close to zero. In the region of the calibration curve where the slope is 

nearly zero (saturation region), the accuracy of the data reduction method is 

considerably reduced. That is, a small error in normalized reflectance can produce a 

large error in dye mass. Thus, the saturation region limits the usable range of the 

calibration curve. The usable range of the calibration curve corresponds to the region of 

the curve where small errors in reflectance measurements do no result in large errors in 

dye mass per unit area. It is desirable to have a reflectance calibration curve with a wide 

usable range because during testing, a range of dye densities is usually obtained on the 

blotter strips due to the variation in test conditions and impingement intensity. 

NASA/TM—2002-211700 40
 Figures 69 and 70 show that the start of the saturation region for the VG80# 

occurred at a dye mass density near 1.5 g/cm2

. For the VG100# and W3MM papers the 

saturation range occurred at dye mass densities greater than 2.5 g/cm2. Thus, the 

VG100# and W3MM papers were selected for further evaluation during for the 1997 IRT 

impingement tests. Tests with a number of airfoil models showed that the W3MM was 

easier to apply to the model surface. Its resistance to dye penetration, however, was low 

and in many cases the level of dye penetration was high even for short spray times. 

The VG100# paper was prone to creasing in regions of high surface curvature such as 

the sharp leading edge of a thin airfoil. However, this paper was considerably more 

resistant to dye penetration and it provided the best overall performance during the 

impingement tests. The VG100# paper was used exclusively for all impingement tests 

conducted in 1999. Note that the spray duration and the concentration of the blue dye 

solution were determined from the reflectance and penetration characteristics of the 

VG100# blotter paper used in the impingement tests. 

7.2.2 Blotter Paper Illumination 

 To eliminate the influence of external light sources on reflectance measurements, 

the data reduction was performed in a dark room. Thus, the only light source was that 

used in the illumination of the blotter strips. 

The laser reflectometer relies on a point measurement technique and the 

illumination of the blotter paper is accomplished using a He-Ne laser beam 1mm in 

diameter. For practical purposes, the intensity of the incident light over the 1mm 

diameter area of the blotter paper can be assumed uniform. Laser light intensity could 

be affected by variations in laser power output. However, this problem was eliminated 

with the use of the glass splitter plate shown in Fig. 51a. Details on the use of the splitter 

plate to account for laser power fluctuations during the data reduction process can be 

found in Ref. 6. Another advantage of the laser reflectometer is that the intensity of the 

laser beam is powerful enough to penetrate below the surface of the blotter paper. Thus, 

reflectance measurements are less sensitive to dye penetration as long as dye 

penetration into the blotter is limited to less than 20% of the blotter thickness. 

The CCD data reduction method measures reflectance over a large area of the 

blotter strip simultaneously. For this system, uniform illumination of the blotter strip is 

very important in obtaining accurate results. In addition, dye penetration into the paper 

can affect the accuracy of the reflectance measurements because the illumination 

intensity from the four halogen lamps used to in the CCD system was not high enough 

to penetrate below the surface of the blotter paper. Thus, dye penetration into the blotter 

must be maintained to very low levels when the CCD data reduction system is used to 

extract the impingement data. 

7.2.3 Repeatability of Data Reduction Systems

To establish the repeatability of the data reduction systems, a white VG100# 

blotter strip was scanned with the laser and the CCD reflectometers several times over a 

period of two months. Four randomly selected scans obtained with each data reduction 

NASA/TM—2002-211700 41
system are presented in Figs. 71 and 72 for 1997 and 1999 tests respectively. The 

results indicate that the variation in the four reflectance measurements obtained with the 

laser reflectometer and the CCD system was approximately ±1% from the average. 

7.3 Pressure Distributions 

 Experimental pressure distributions for the all models tested are compared with 

analysis results from LEWICE-2D, LEWICE-3D, INS2D and NPARC in Figs. 73–82. 

Note that the first two computer codes use potential flow methods for the computation of 

the flow field. INS2D is an incompressible Navier-Stokes code while NPARC uses the 

full Navier-Stokes equations to simulate internal or external flows. In order to match the 

experimental pressure, the angles of attack in the computations were slightly adjusted 

by approximately –2.0 to 2.5 degrees depending on the model tested. The adjustments 

made in the angles of attack used in the computations of the airfoil/wing flow fields were 

mainly due to airfoil trailing edge thickness, viscous effects and tunnel wall effects. For 

example, the trailing edge of the MS(1)-0317 was blunt with a thickness of 

approximately 1% chord, however, for the computations, a sharp trailing edge was 

generated by extending the airfoil chord. This extension resulted in higher circulation for 

a given angle of attack. Another reason for the reduction in angle of attack used in the 

computations is tunnel flow angularity, which was found to be approximately –0.5°. 

Good correlations can be found for all cases between experimental and computational 

data after modifying the computational angles of attack. 

Experimental and computational pressure distributions for the multi-element airfoil 

are depicted in Fig. 81. The flow computations were performed with the INS2D computer 

code (Refs. 47, 48) using a Chimera grid. For this case, acceptable correlation between 

the experimental and computational results was obtained without having to modify the 

experimental angle of attack. The discrepancies observed over the slat surface could be 

due to the small tunnel angularity and tunnel wall effects. 

 Experimental and computed pressure distributions for the S-Duct engine inlet are 

presented in Figs. 82a–82c for a freestream velocity of 170 mph and an inlet mass flow 

of 23 lbm/sec. The computed pressure distributions were obtained with the NPARC 

Navier-Stokes code (Ref. 49). Good agreement between experiment and analysis is 

demonstrated at most inlet locations. However, for the axial location X=37.24 in Fig. 

82c considerable differences between the computed and experimental pressure 

distributions were observed. 

7.4 Impingement Results 

7.4.1 Test Repeatability

Test repeatability is an important indicator of the quality of the experimental 

results. For the purpose of this discussion, repeatability is defined as the maximum 

percent difference of repeated tests from the average. Typical test repeatability in 

previous experimental investigations (Refs. 1–6) was in the range 10% to 30%. The 

large variation in the test data was attributed to a number of factors that influence the 

experimental results as discussed in Refs. 1, 2, 6, 30 and 50. A discussion of potential 

sources of errors affecting the impingement data was presented in sections 7.1 and 7.2. 

NASA/TM—2002-211700 42
During the 1997 and 1999 impingement tests, 3 to 4 tests were performed for 

each test condition and in a limited number of cases as many as 11 tests were 

conducted to assess the repeatability of the experimental data. Selected test 

repeatability data are presented in Figs. 83–94 and in Table 15 for all eleven models 

tested during the 1997 and 1999 IRT entries and for most of the test conditions. The 

results presented in these figures indicate that the maximum difference of repeated 

tests from the average was as follows: 

• MS(1)-0317 airfoil (1997 IRT tests) 3.0% to 12.0% 

• MS(1)-0317 airfoil (1999 IRT tests) 3.0% to 11.0% 

• GLC 305 airfoil 4.9% to 16.0% 

• NACA 652-415 airfoil 7.0% to 17.0% 

• Commercial Transport Tail Section 1.7% to 9.8% 

• NLF-0414 (36-inch chord) 0.2% to 14.0% 

• NLF-0414 (48-inch chord) 0.8% to 11.0% 

• NACA 64A008 Swept Tail 3.2% to 12.0% 

• 25%-Scale Business Jet Horizontal Tail 3.2% to 14.0% 

• Full-Scale Business Jet Horizontal Tail 1.6% to 8.7% 

• Three-element High Lift System 5.6% to 17.0% 

• S-Duct Engine Inlet 4.6% to 13.0% 

In summary, the data presented indicate that the maximum difference of 

repeated tests from the average was 

• 0.24% to 12% for 82 out of the 93 cases presented 

• 13.00% to 17% for 11 out of the 93 cases presented 

For the test conditions where 11 tests were performed to assess test 

repeatability, the maximum difference from the average was similar to that obtained 

using only 3 to 4 test runs. 

 

 This is a significant improvement in test repeatability compared to previous 

experimental efforts. The effort to improve the repeatability of the experimental 

impingement data continues. Currently, work is being done to further enhance the 

accuracy of the data reduction methods and to develop new methods for measuring 

local LWC in the vicinity of the test model using a laser sheet method. 

All experimental data presented in Figs. 83-94 were reduced with the laser 

reflectometer. Note that the laser reflectometer uses point reflectance measurements at 

two to three locations along the width of a blotter strip (see Fig. 52a) to generate the 

value of the local impingement efficiency. Thus, impingement results obtained with the 

laser reflectometer tend to exhibit larger variation from the average. Corresponding 

repeatability data (not shown) obtained with the CCD data reduction system exhibited 

less variation from the average by approximately 1 to 2 percentage points compared to 

the laser reflectometer. This is because at any model surface location the CCD system 

NASA/TM—2002-211700 43
averages data from a large portion of the width of the blotter strip which reduces the 

effect of local variations in impingement characteristics between test runs. The laser 

illumination method used in the laser reflectometer, however, can penetrate below the 

surface of the blotter paper and as a result, dye penetration errors are minimized as 

explained in section 5 of this report. 

7.4.2 Experimental and LEWICE Impingement Data

All the experimental impingement curves presented in this section are the 

average of the three to four tests conducted for each impingement condition. Prior to 

averaging the experimental data, the individual experimental impingement curves were 

smoothed using a three point moving average technique. Unless stated otherwise, the 

experimental impingement data presented were reduced using the laser reflectometer. 

A summary of key geometric as well as aerodynamic and impingement 

parameters for the two-dimensional airfoils and the three finite wing model tested are 

provided in Table 16. The symbol Sβmax in Table 16 denotes the surface location 

corresponding to the maximum impingement efficiency. The symbols Su and Sl

 are the 

upper and lower impingement limits defined as the locations on the model surface 

where the local impingement efficiency was 0.01% (i.e., β = 0.0001). The nondimensional chordwise locations for Su and Sl are denoted by xu/c and xl

/c. 

Experimental impingement data for the eleven models tested and for all test 

conditions are compared with LEWICE-2D and LEWICE-3D predictions in Figs. 95–107. 

For ease of reference, a summary of all impingement data obtained during the 1997 and 

1999 IRT tests is provided in Appendix A. The impingement data are presented in the 

form of local impingement efficiency versus surface distance in mm. Surface distance 

was measured with respect to a reference point on each test model termed the 

highlight. Surface distance was negative along the suction side (typically the airfoil 

upper surface) and positive along the pressure side of an airfoil or finite span tail model. 

For all models tested, the highlight was located at the leading edge corresponding to a 

surface distance of 0 mm. The surface distance resolution for the experimental data 

was 0.50 mm (0.02 inch). For clarity of presentation, symbols were placed at every 5th 

point in the experimental curves. Caution was exercised in the placement of these 

symbols so as not to miss the location of the peak efficiency. 

With the exception of the S-duct case, the LEWICE impingement results 

presented in the figures were obtained with the measured FSSP+OAP droplet 

distributions shown in Fig. 42 which were divided into 27 bins to simplify the 

computations. Note that the version of LEWICE distributed to the public is limited to a 

maximum of 10 bins for approximating droplet distributions. For the S-duct inlet an 8-

bin approximation of the experimental droplet distributions was used. For the LEWICE 

computations the experimental angles of attack were adjusted as discussed in section 

7.3 to match the experimental pressure distributions. 

 Figures 108–116 show experimental impingement limits plotted on the airfoil 

surface for the six two dimensional test models and the three finite tail models tested. 

NASA/TM—2002-211700 44
Figures 117–125 show the experimental impingement distributions plotted on the airfoil 

surface. These plots are for illustration purposes only and they are not to scale. The 

plots were constructed by plotting the local impingement efficiency value at a given 

surface location normal to the surface of the airfoil. All β values were scaled by c/20 

where c is the chord length of the airfoil in mm. The resulting plots resemble ice 

accretions and are useful in demonstrating the magnitude and extent of impingement as 

a function of angle of attack and MVD size. 

A. MS(1)-0317 Airfoil 

This airfoil was tested by the WSU/Boeing research group in 1985 and it was 

used as a calibration model for the IRT impingement tests conducted in 1997 and 1999. 

Comparisons between test data obtained in 1985 and in 1997 were presented in Ref. 50 

and showed good overall agreement. 

Experimental impingement data at the mid-span location (36 inches above the 

tunnel floor) of the MS(1)-0317 airfoil are presented in Figs. 95a–95f for angles of attack 

of 0° and 8° and MVDs of 11.5, 21 and 92μm. The data presented in Fig. 95 were 

obtained during the 1997 IRT entry. For all cases, three impingement curves are 

presented for each angle of attack. Two of the curves are the experimental data reduced 

with the CCD data reduction system and the laser reflectometer while the third curve is 

analysis data obtained with the LEWICE-2D code. The computations were performed 

for an angle of attack of -1.85° (instead of 0°) and for 6.15° (instead of 8°) to match the 

experimental pressure distributions as shown in Fig. 73. The experimental data obtained 

in 1999 for an angle of attack of 0° and MVDs of 11, 21 and 94 micron are presented in 

Fig. 96. The experimental and analytical impingement efficiency distributions presented 

in Figs. 95 and 96 indicate the following general trends: 

1. Experimental data reduced with the laser reflectometer and the CCD data 

reduction systems were in very good overall agreement. In some cases, 

however, the laser reflectometer produced higher impingement efficiency values 

near the region of maximum impingement efficiency. This is evident in the 1997 

data presented in Fig. 95. The reason for the observed discrepancy was 

attributed to a small level of dye penetration into the blotter, which could not be 

detected by the current set up of the CCD data reduction system. In 1999, the 

spray times were reduced to minimize dye penetration into the blotter. Note that 

the 1999 experimental impingement data obtained with the laser and CCD 

reflectometers are in better overall agreement compared to the 1997 data. 

2. For the α = 0° case, the maximum impingement efficiency occurred along the 

upper surface (s = –1 to –6 mm) near the leading edge for all MVDs. Maximum 

values of β were 0.32–0.33 (laser), 0.26 (CCD) for MVD = 11.5 and 11μm; 0.50 

(laser), 0.41 (CCD) for MVD = 21μm; 0.68 (laser), 0.59 (CCD) for MVD = 92 and 

94 μm. The extent of the impingement limits increased with MVD size as 

expected. 

NASA/TM—2002-211700 45
3. At the higher angle of attack, α = 8°, the location of maximum impingement 

efficiency was shifted to the lower surface of the airfoil. For this case, the values 

of maximum β were 0.25 for MVD = 11.5 μm, 0.51 for MVD = 21 μm, and 0.76 

for MVD = 92 μm. Once again, the extent of the impingement limits increased 

with MVD size. 

4. Analysis results obtained with the corrected angles of attack and with the 

measured droplet distributions (solid line) were in good correlation with the 

experimental results for the 11-μm, 11.5-μm and 21-μm MVD cases. However, 

for the 92-μm and 94-μm MVDs, the computed impingement efficiencies were 

considerably higher and the impingement limits were greater than the 

experiment. 

5. Analysis impingement data obtained with uncorrected angles of attack (not 

shown) were shifted to the right with respect to the experimental data. 

6. Experimental data obtained in 1997 and in 1999 for α = 0° and MVDs of 11, 

11.5, 21, 92 and 94 microns were in very good agreement in all cases as shown 

in Fig. 97 indicating that the experimental methodology was consistent and 

repeatable. 

B. GLC 305 Airfoil Section 

Experimental and LEWICE impingement data for angles of attack of 1.5° and 6°

and MVDs of 11.5, 21 and 92 micron are compared in Figs. 98a–98f. All data are for the 

mid-span station (36 inches above the tunnel floor) and were obtained during the 1997 

IRT entry. The LEWICE computations presented were obtained for angles of attack 1.6°

and 5.25° to match the experimental pressure distributions as shown in Fig. 74. The 

measured FSSP+OAP droplet distributions were used to compute the impingement 

characteristics. For both angles of attack tested, good agreement between LEWICE and 

experiment is demonstrated for the 11.5 and 21-micron MVD cases but once again, 

large differences are observed for the 92-micron case. The maximum impingement 

efficiency for the α = 1.5° was on the lower surface of the airfoil in the proximity of the 

leading edge. Maximum experimental impingement efficiencies for this angle of attack 

were 0.47, 0.66 and 0.76 for the 11.5, 21 and 92-micron MVDs respectively. For all MVD 

cases the extent of impingement was greater on the lower surface than on the upper 

surface as shown in Figs. 98a–98c. For the case of α = 6°, the location of the maximum 

impingement efficiency was further aft on the lower surface as expected and the 

maximum experimental impingement efficiencies were 0.43, 0.60 and 0.72 for the 11.5, 

21 and 92-micron MVDs respectively. 

C. NACA 652-415 Airfoil 

Experimental and LEWICE impingement data for this airfoil obtained at the midspan location (36 inches above the tunnel floor) during the 1997 IRT entry are presented 

in Figs. 99a–99c for α = 0° and in Figs. 99d–99f for α = 8°. The LEWICE computations 

presented in Figs. 99a–99f were obtained for angles of attack –0.55° and 6.55° to match 

the experimental pressure distributions as shown in Fig. 75. 

NASA/TM—2002-211700 46
For the α = 0° case, the point of maximum impingement for this airfoil was at the 

leading edge and the maximum impingement efficiency was 0.45, 0.62 and 0.73 for the 

11.5, 21 and 92-micron cases respectively. As expected, the impingement limits 

increased with MVD size. Overall, agreement with the LEWICE was very good for the 

11.5-μm case. For the 21-μm MVD, the LEWICE impingement tails were higher in 

magnitude and extent than the experimental data. Notable differences were observed 

between LEWICE and experiment for the 92-μm MVD case. The magnitude and extent 

of impingement computed by LEWICE were considerably greater than the experiment 

for this MVD. 

As angle of attack was increased to 8°, the following trends were observed in the 

experimental data. The point of maximum impingement moved toward the lower surface, 

maximum impingement efficiency decreased with respect to the α = 0° case for all 

MVDs and the limit of impingement moved toward the leading edge on the upper 

surface and toward the trailing edge on the lower surface. Agreement with the LEWICE 

data was good for the 11.5 and 21-micron cases. For the 92-μm case, large 

discrepancies between the LEWICE and the experimental data were observed. Once 

again, the analysis produced more water impingement than the experiment. 

D. Commercial Transport Tail Section 

Experimental results from the 1997 IRT entry and LEWICE data for this model 

are compared in Figs. 100a-100f for an angle of attack of 0° and 4°. The experimental 

results correspond to the mid-span station (36 inches above the tunnel floor). The 

LEWICE computations presented in Figs. 100a-100f were obtained for angles of attack 

0° and 4°. Note that for this airfoil the experimental and computational angles of attack 

were the same as shown in Fig. 76. Correlation between experimental and analysis was 

good for MVDs of 11.5 and 21 microns for both angles of attack. The 92-micron data 

show the same discrepancy between analysis and experiment that was observed with 

the other test models. The maximum experimental impingement occurred at the leading 

edge for α = 0° for all MVDs with maximum impingement efficiency of 0.47, 0.60 and 

0.76 for the 11.5, 21 and 92-micron cases respectively. At α = 4° the impingement 

curves shifted toward the lower surface and the maximum impingement efficiency 

values were 0.41, 0.54 and 0.74 for 11.5, 21 and 92-micron spray clouds respectively. 

E. 36-in and 48-in NLF(1)-0414 Airfoils 

Two airfoils with chordlengths of 36 and 48 inches were tested in 1999 to provide 

impingement data for two different scales. In addition, the 48-in airfoil had a 25% chord 

control surface to measure the effect of simple flap or aileron deflection on impingement 

characteristics. The experimental and LEWICE data presented in Figs. 101a–101f are 

for the 36-inch airfoil and include angles of attack of 0° and 8° and all MVD cases 

tested. For the 48-inch airfoil, the experimental and LEWICE data are presented in Figs. 

102a-102o and include α = 0°, 4°, and 8° with a flap deflection of δ = 0° and α = 0° with 

a flap deflection of δ = 15°. Note that the experimental data shown in the figures 

correspond to the mid-span location. The angles of attack used in the LEWICE 

NASA/TM—2002-211700 47
computations to match the experimental pressure distributions for α = 0°, and 8° with a 

flap deflection of δ = 0° were as follows: –1° and 5.5° for the 36 inch chord model and -

0.75° and 6° for the 48-inch model as shown in Figs. 77 and 78 respectively. 

Experimental and LEWICE impingement data for an angle of attack of 0 degrees 

and for MVDs of 11, 21 and 94 micron are compared in Figs. 101a–101c and 102a–

102c for the 36-in and 48-in airfoils respectively. Maximum impingement efficiency for 

the 36-in airfoil was 0.45, 0.60, and 0.77 for the 11, 21 and 94-micron cases 

respectively. Corresponding maximum impingement efficiencies for the 48-in airfoil were 

0.40, 0.55 and 0.75. Thus, for each MVD case the 36-inch airfoil had higher maximum 

impingement efficiency and the impingement limits were further aft (in percent chord) 

than the 48-inch section as expected. For both airfoils and for all MVDs the maximum 

impingement efficiency occurred at the upper surface close to the leading edge. Good 

agreement between the experimental and LEWICE data was demonstrated for the 21-

micron case. For the 11-micron case, however, the maximum experimental impingement 

efficiency was approximately 6% higher for the 36-inch airfoil and 12% higher for the 48-

in airfoil than corresponding LEWICE values. The experimental data for the 94-micron 

MVD had considerably smaller impingement limits and maximum impingement efficiency 

than the LEWICE results. 

Experimental and LEWICE impingement data for an angle of attack of 4 degrees 

and for MVDs of 11, 21 and 94 micron are compared in Figs. 102d–102f for the 48-in 

airfoil. Maximum impingement efficiency for this case was 0.38, 0.52, and 0.72 for the 

11, 21 and 94-micron cases respectively. Good agreement between the experimental 

and LEWICE data was demonstrated for all but the 94-micron case. 

Experimental and LEWICE impingement data for an angle of attack of 8° and for 

MVDs of 11, 21 and 94 micron are compared in Figs. 101d–101f and 102g–102i for the 

36-inch and 48-inch airfoils respectively. Maximum impingement efficiency for the 36-in 

airfoil was 0.37, 0.57, and 0.75 for the 11, 21 and 94-micron cases respectively. 

Corresponding maximum impingement efficiencies for the 48-inch airfoil were 0.36, 0.51 

and 0.70. As observed with the α = 0° case, for fixed MVD the 36-inch airfoil had higher 

maximum impingement efficiency and larger impingement limits (in percent chord) than 

the 48-inch section as expected. For both airfoils and for all MVDs the maximum 

impingement efficiency moved further aft along the lower surface as the angle of attack 

was increased from 0 to 8 degrees. For the 36-inch airfoil, good correlation between the 

LEWICE and the experimental data was demonstrated for the 11 and 21-micron cases 

but not for the 94-micron case. In the case of the 48-inch section, LEWICE produced 

lower impingement efficiencies than the experiment for the 11-micron case. In general, 

good agreement between the experiment and analysis was observed for the 21-micron 

case. For the 94-micron case, the impingement efficiency obtained with LEWICE was 

considerably higher than the experiment. 

Referring to Figs. 101e, 102e and 102h corresponding to test cases α = 8°, 

MVD=21 μm, 36-inch section, α = 4°, MVD=21 μm, 48-inch section, and α = 8°, 

NASA/TM—2002-211700 48
MVD=21 μm, 48-inch section a small "hump" was observed in the experimental 

impingement data between S=30mm and S=90 mm. The LEWICE data did not exhibit 

this feature. The reason for this difference between the analysis and the experiment is 

not known. 

The effect of the 25% chord flap deflection on the impingement characteristics of 

the 48-inch NLF(f)-0414 airfoil is shown in Figs. 102j–102o. The data presented in these 

figures are for an angle of attack of 0 degrees and a flap deflection of 15 degrees trailing 

edge down. The peak impingement efficiencies for this case were 0.41, 0.55 and 0.75 

for the 11, 21 and 94-micron cases respectively. Note that these values are nearly the 

same as the ones obtained with the flap at 0 degrees. However, the flap deflection 

caused the location of the maximum impingement efficiency to move from 2 mm along 

the upper surface to 6 to 7 mm along the lower surface. In addition, the impingement 

curve was shifted to the right as a result of deflecting the flap. Good agreement between 

the experimental and LEWICE data was demonstrated for all but the 94-micron case. 

Figures 102k, 102m and 102o show the impingement distribution on the lower surface of 

the flap element for the 11, 21 and 94-micron cases respectively. In all cases, droplet 

impingement extended to the trailing edge of the flap and the impingement intensity 

increased as the cloud MVD was increased. 

F. NACA 64A008 Finite Swept Tail 

This model was tested during the 1997 IRT entry. Impingement data for this 

reflection plane model were obtained at two stations A (inboard) and B (outboard) 

corresponding to 36 and 44 inches above the tunnel floor respectively. The chord 

lengths at stations A and B were 32.76 inch and 29.52 inch respectively. Station B was 

approximately 5 inches from the tail tip. All blotter strips were V shaped to permit 

alignment of the blotters with the streamwise direction. 

Analysis data for this geometry were obtained with the LEWICE-3D code. 

Experimental data reduced with the laser reflectometer are provided for station A only. 

Data for station B were practically the same as that for station A and have not been 

plotted. Analysis data are provided for both the A and B locations. The experimental 

data are for angles of attack of 0 and 6 degrees and for all three cloud MVDs. 

In Figs. 103a–103c, the experimental results are compared with computational 

data for an α of 0°. The correlation is good for the 11.5 and 21-micron cases but not for 

the 92-micron MVD. The maximum impingement efficiencies for all MVDs occurred at 

the leading edge as expected for a symmetric airfoil. The magnitudes of the peak 

efficiencies in the experimental data were 0.45, 0.61 and 0.71 for the 11.5, 21 and 92-

micron cases respectively. LEWICE-3D computations showed very small differences 

between the impingement efficiency distributions obtained at stations A and B. 

Impingement results for α = 6° are presented in Figs. 103d–103f. The 

experimental results show a shift in the impingement curves toward the lower surface of 

the tail. The maximum impingement efficiencies occurred on the lower surface near the 

leading edge and had magnitudes of 0.45, 0.61 and 0.70 for the 11.5, 21, and 92-micron 

NASA/TM—2002-211700 49
cases respectively. Agreement between analysis and experiment was good for the 11.5 

and 21-micron MVDs but not for the 92-micron case where the analysis predicted 

substantially higher impingement values and larger impingement limits. Once again no 

notable differences between the station A and B results were observed in the LEWICE3D data presented. 

G. 25%-Scale Business Jet Empennage (BJE) 

This model was tested in 1999 to obtain impingement data for the horizontal tail 

of a modern business jet. In general, tailplanes are inverted wings so that the suction 

side of the airfoil corresponds to the lower surface of the tail while the pressure side 

of the airfoil is the upper surface of the tail. Typically, tailplanes operate at negative 

angles of attack for downward (i.e., negative) lift so as to balance the aircraft in 

pitch. The horizontal tail was set at –8 degrees with respect to the body axis. Thus, 

a body angle of attack, αb, of +8° corresponded to a geom etric tail angle of attack, 

αt, of 0°. The horizontal tail was tested at two tail angles of attack, αt = –1 and –6 

degrees. 

Impingement data were obtained using V-shape blotter strips at two spanwise 

locations A and B corresponding to the 25.5% and 55.4% tail semi-span locations as 

shown below: 

• A (Inboard) : 19.2-in from the tail tip, (25.78–19.2)/25.78=0.255 semi-span 

• B (Outboard) : 11.5-in from the tail tip, (25.78–11.5)/25.78=0.554 semi-span 

These spanwise locations were selected because the tail was instrumented with 

pressure taps at these locations to provide pressure information for the validation of the 

computed flow field used in the impingement analysis. Another constraint in the 

selection of these spanwise locations was that they had to be within the region of cloud 

uniformity. 

 Experimental and LEWICE-3D impingement data for this model are compared in 

Figs. 104a–104c (inboard location) and in 104g-104i (outboard location) for a tail angle 

of attack of –1° and in Figs. 104d–104f (inboard location) and in 104j–104l (outboard 

location) for a tail angle of attack of –6°. Note that in these figures, the surface distance 

from the highlight is divided into "Suction Side" and "Pressure Side" instead of "Upper 

Surface" and "Lower Surface". For all other airfoil and finite span tail geometries tested, 

the lower surface of the airfoil or tail was the pressure side. However, since the 25%-

scale horizontal tailplane was tested as an inverted wing the pressure side was the 

upper surface. 

LEWICE-3D computations were performed for tail angles of attack of –2 and –7 

degrees instead of the experimental values of –1 and –6 degrees to match the 

experimental pressure distributions as shown in Fig. 80. 

 The maximum collection efficiency and the extent of impingement increased with 

increasing drop size and the impingement region was shifted towards the pressure side 

NASA/TM—2002-211700 50
of the tail as the tail angle of attack was increased (more negative). Good overall 

agreement between the LEWICE-3D and the experiment impingement data was 

observed in all cases tested except for the 94-micron MVD cases. The experimental 

and computational impingement results for the two spanwise stations were nearly the 

same for all MVDs and angles of attack tested. The maximum experimental collection 

efficiencies for the 25%-scale model ranged from 0.6 to 0.81 as the cloud MVD was 

increased from 11 to 94 microns. Peak efficiencies were 1% to 4% higher for the –1 

degree tail angle of attack case than for the –6 degree case. The high impingement 

peak efficiencies obtained with this model were attributed to its small chord length and 

to its thin profile which had a maximum thickness to chord ratio of 0.08. 

H. Full-Scale Business Jet Tail Section 

The left side (with respect to the pilot) of a full-scale business jet horizontal tail 

was tested in 1999 to provide full-scale data for the 25%-scale horizontal tail model 

discussed above. The geometric characteristics of the 25%-scale and the full-scale tails 

were identical. The semi-span of the full-scale horizontal tail was 103.16 inches and 

was considerably larger than the height of the tunnel, thus the tail was truncated at 

approximately 44.5% semi-span so that it could be installed in the IRT test section as a 

reflection plane model. The truncated half tail model was the outboard 57-inch portion 

(44.5% to 100% semi-span) of the non-truncated full-scale half tail. 

Impingement data were obtained using V-shape blotter strips at two tail spanwise 

locations A and B corresponding to the 72.4% and 79.6% tail semi-span locations of the 

non-truncated model as shown below: 

• A (Inboard) : 28.5-in from the tail tip, (103.16–28.5)/103.16=0.724 semi-span 

• B (Outboard) : 21.0-in from the tail tip, (103.16–21.0)/103.16=0.796 semi-span 

These spanwise locations were selected to be within the uniform cloud region. In 

addition, the inboard loaction was selected to match as close as possible the outboard 

location tested with the 25%-scale model which was at 55.5% semi-span. The 

difference between the inboard location on the full-scale and the outboard location 

tested with the 25%-scale model was approximately 17% semi-span which was 

considerable. However, experimental impingement data obtained with the NACA 

64A008 and the 25%-scale swept tail models showed little variation in the impingement 

distributions with spanwise location over a considerable spanwise distance. Thus, 

considering the test constraints associated with full and sub-scale model testing in the 

same wind tunnel facility, it was felt that the comparison of the the full-scale tail data 

obtained at the 72.4% semi-span station with the 25%-scale data obtained at the 55.5% 

semi-span could provide useful information regarding scaling effects. 

 Another significant difference between the full-scale and sub-scale models was 

the chord Reynolds number because both models were tested at the same air speed. 

The Reynolds number of the truncated full-scale model was 4.3 million while that of the 

25%-scale model was 1.49 million. However, because the tests were conducted at low 

tail angles of attack, and the Reynolds numbers were in the turbulent range for both 

NASA/TM—2002-211700 51
models the difference between the two test model flow fields were not significant, even 

though the difference in Reynolds number for the two models was considerable. Finally, 

it should be noted that the truncated full-scale tail had a lower aspect ratio than the full 

span 25%-scale model. However, studies performed with computational flow dynamics 

showed that the effect of lowering the model aspect ratio on the pressure distribution at 

the impingement locations tested was small for the low angles of attack used in this 

study. 

Experimental and LEWICE-3D impingement data for the truncated full-scale 

horizontal tail are presented in Figs. 105a–105h for all test configurations and tail 

spanwise locations. The results presented indicate the following: 

1. Spanwise location had a small effect on the impingement distributions. In general 

the peak impingement efficiencies were in the range 0.44 to 0.75. 

2. LEWICE and experimental data were in good agreement for the 11 and 21-

micron MVD cases but not for the 94-micron MVD case. 

3. Only the 21-micron MVD was tested for the 6 degree tail angle of attack case. 

For this case, the impingement curves were shifted to the right as the angle of 

attack was increased from 1 to 6 degrees indicating more impingement on the 

lower surface (pressure side) of the tail as expected. The peak impingement 

efficiencies, however, did not change with angle of attack as shown in Table 16. 

Comparison of full-scale impingement data obtained at the 72.4% (inboard) semispan location (Figs. 105a–105c and 105d ) with corresponding 25%-scale data obtained 

at the 55.5% (outboard) semi-span station (Figs. 104g–104i and 104k) showed that the 

peak efficiencies where higher for the sub-scale model by 18% for the 11-micron MVD 

case, 15% for the 21-micron MVD case and 10% for the 94-micron MVD case. In 

addition, the chordwise extent of impingement for the sub-scale model was greater in all 

cases as demonstrated in Table 16. 

I. Three-element High Lift System 

 This model was tested during the 1997 IRT entry. Experimental impingement 

data for this model are presented in Figs. 106a–106v. The experimental data presented 

are for α = 0° and 4° with slat deflection of 30° and flap deflection of 30° (i.e., landing 

configuration, see Fig. 17a). The highlight location corresponding to a surface distance, 

S, of 0 mm, was at the leading edge of each element. 

LEWICE-3D impingement data were obtained for α = 0° only since analysis flow 

field data were not available for the 4 degree angle of attack case. The flow field about 

this model was computed using the INS2D incompressible Navier-Stokes code 

(Refs. 47 and 48). The LEWICE-3D computations were performed with the measured 

(FSSP+OAP) droplet distributions which were divided into 27-bins for the impingement 

computations. Impingement analysis data are presented for all three elements. 

Experimental and analysis data for α=0° and MVDs of 11.5, 21 and 92 microns 

are compared in Figs. 106a through 106k. In most cases, the computed and 

NASA/TM—2002-211700 52
experimental impingement efficiency distributions for the slat and flap elements were in 

good agreement. For the main element, however, the LEWICE results were 

considerably higher than the experimental data. The reason for this discrepancy is not 

clear. 

The experimental data show that βmax for all MVD cases occurred near the 

leading edge of the slat. The impingement intensity on the main element was very low 

and in general the impingement efficiency was less than 10%. The impingement limits 

for the main element varied from the upper surface to the start of the cove region (step) 

on the lower surface. In general, droplet impingement in the cove region of the main 

element occurred near the trailing edge for the 11.5 and 21-micron cases only. The 

extent of impingement in the cove region was approximately 30 to 50 mm long and the 

magnitude ranged from nearly zero to approximately 0.15 for the 11.5-micron case and 

to 0.05 for the 21-micron case as shown in Figs. 106j and 106k respectively. In both 

cases, the maximum impingement occurred at the trailing edge of the main element. 

The impingement limit for the lower surface of the flap extended to the flap trailing edge. 

In general, the LEWICE results for the slat and flap elements exhibited the same trends 

as those observed in the experimental data. Discrepancies between the experimental 

and the computed impingement data for the slat and flap elements were mainly due to 

differences in the experimental and computational flow fields. Multi-element flow fields 

pose significant challenges for flow analysis tools due to the complex viscous flow 

regions that develop in the gaps between adjacent elements. It is interesting to point out 

that the LEWICE impingement data for the 92-micron case exhibited better agreement 

with the experimental data for this model compared to the other models tested. 

Furthermore, for the 92-micron case the magnitude of the impingement efficiencies 

predicted by LEWICE for the flap element were less than the experimental values. 

Experimental impingement data for α = 4° and MVDs of 11.5 and 21 and 92 

micron are presented for the slat, main and flap elements in Figs. 106l–106v. The 

maximum impingement on the slat and flap did not vary significantly from the α = 0°

case while the maximum impingement on the main element increased significantly as 

demonstrated in Figs. 106o–106q and in Table 17. The impingement limit on the lower 

surface of the flap extended to the trailing edge of this element for all MVD cases 

tested. In general, for the 4 degrees angle of attack case, droplet impingement in the 

cove region of the main element was similar to that observed for the α = 0° case as 

shown in Figs. 106u and 106v for the 11.5 and 21-micron cases respectively. 

J. S-Duct Engine Inlet 

Experimental impingement data for this inlet were obtained during the 1999 IRT 

entry for the following test cases: 

1. α= 0°, V = 170 mph, MVD = 11, 21, 94 micron 

Main inlet Flow = 23 lb/s, Scavenge Flow =2.08 lb/s 

Capture Area Ratio (CAR) = 0.60 (does not include scavenge flow) 

Capture Area Ratio (CAR) = 0.65 (includes scavenge flow) 

Blotter Strip Locations: A, B, C, D 

NASA/TM—2002-211700 53
2. α= 0°, V = 130 mph, MVD= 21, 94 micron 

Main inlet Flow = 23 lb/s, Scavenge Flow =1.57 lb/s 

Capture Area Ratio (CAR) = 0.80 (does not include scavenge flow) 

Capture Area Ratio (CAR) = 0.84 (includes scavenge flow) 

Blotter Strip Locations: A, B, C, D 

The locations of the four blotter strips A, B, C and D are shown in Fig. 22h and 

where as follows: 

Strip A: Inlet outer lip at circumferential location θ = 180°. For this strip S=0 mm 

(highlight) in the impingement plots corresponds to the highlight of the engine 

outer lip. 

Strip B: Inlet interior sidewall at circumferential location θ = 90° extending from 10.7 to 

27.6 inches in the axial direction with respect to the inlet outer lip highlight.

Strip C: Apex corner (also referred to as splitter nose) at axial location x = 27.5 inches 

with respect to the inlet outer lip highlight. For this strip, S=0 mm in the 

impingement plots corresponds to the most forward (upstream) point on the 

apex corner. The strip was used to obtain impingement data along a section on 

the inlet vertical plane of symmetry on the splitter surface dividing the main flow 

from the scavenge flow. 

Strip D: Lower surface of torque tube in engine duct at circumferential location θ = 180°

extending from 27.5 inches to 37.5 inches with respect to the inlet outer lip 

highlight. For this strip, S=0 mm in the impingement plots corresponds to the 

downstream end of the blotter strip which was located behind the small ramp on 

the torque tube at an axial location 28 inches form the inlet outer lip highlight as 

shown in Fig. 22h. 

 The experimental impingement data presented in Figs. 107a–107o indicate the 

following: 

• Test Case 1 (CAR=0.65): The experimental data presented in Figs. 107a–107c 

indicate that water impingement at locations A and B increased progressively as the 

droplet size was increased from 11 to 94 microns. Note that for the 11-micron case 

practically no impingement was observed along the inlet side wall (Strip B). The 

maximum and total impingement at location C (splitter nose) increased dramatically 

as the cloud MVD was increased from 11 to 94 microns as demonstrated in 

Figs. 107d–107f. Note that most of the impingement occurred on the scavenge duct 

side indicating that the inlet performed as designed; that is the water droplets were 

directed away from the engine by the scavenge flow. Only for the 94-micron case 

was there substantial impingement on the inlet side of the splitter nose surface. The 

experimental data for strip D shown in Figs. 107g–107i indicate considerable total 

impingement on the lower side of the inlet torque tube particularly for the 21 and 94-

micron MVD cases. The maximum impingement intensity occurred near the small 

ramp on the torque tube surface and it did not vary significantly with drop size.

NASA/TM—2002-211700 54
• Test Case 2 (CAR=0.84): the total and maximum experimental water impingement 

intensity at location A increased progressively as the droplet size was increased from 

21 to 94 microns (Figs. 107j–107k). For these two drop sizes, the maximum 

impingement efficiency was 0.45 and 0.58 respectively. Water impingement along 

the interior sidewall of the inlet at location B was nearly zero for the 21-micron MVD 

case and increased to about 10% for the 94-micron case. In general, the total 

impingement at station B was less than for Test Case 1. Water impingement for 

station C (Figs. 107l–107m) exhibited the same trends with MVD size as for the 0.65 

capture area ratio case (Test Case 1). However, both the total and maximum levels 

of impingement efficiency were a little higher for Test Case 2. The impingement 

trends for station D (Figs. 107n–107o) were similar to those obtained with Test Case 

1 but the total and maximum impingement were higher for Test Case 2.

LEWICE-3D computations were performed for Test Case 1 only since analysis 

flow data were not available for Test Case 2. The engine flow field was computed with 

the NPARC Navier-Stokes computer code and was provided by the inlet manufacturer. 

In general, the agreement between LEWICE-3D and experiment was good in terms of 

impingement trends. However, in some cases considerable differences were observed 

between the LEWICE-3D and the experimental impingement intensities and 

impingement limits. These differences are to some extent attributed to differences 

between the computed and the experimental flow fields as demonstrated in Fig. 82. 

7.5 Large Droplet Impingement Issues 

 The comparisons of LEWICE results with the experimental data presented in 

section 7.4 demonstrated good overall agreement for the 11 and 21-micron MVD cases. 

In most cases, however, for the 92 and 94-micron spray clouds LEWICE predicted much 

higher local impingement efficiencies and impingement limits than observed in the 

experiment. Possible reasons for the large differences between analysis and experiment 

are explored in this section. Analysis data and exploratory tests conducted at the 

Goodrich icing tunnel in December of 1998 as well as tests performed during the 1999 

IRT entry are used to support the discussion below. 

7.5.1 Errors in Measuring MVD (92–94 μm cloud)

 A number of computations were conducted to establish the required change in 

cloud MVD in order to match analysis data with the experiment. The assumption was 

that measurement errors with the FSSP and OAP probes may have been the main 

reason for the large differences observed between the analysis and experimental data. 

These studies showed that a reduction of 30–35 microns in the 94-micron MVD size 

would have been necessary in order to bring the analysis data close to the experiment. 

 Even with an MVD of 60 microns, the overall behavior of the analytical 

impingement distribution did not match that of the experiment as shown in Figs. 126–

129. Further reductions in MVD size were investigated but did not improve the 

correlation. For example a 35 micron size MVD would have been necessary to match 

the experimental peak efficiency of the MS-317 airfoil for α = 0° and MVD = 94 μm. 

NASA/TM—2002-211700 55
However, in this case the impingement limits would have been considerably smaller 

than the experiment. In any case, it is very unlikely that the NASA FSSP+OAP 

measurements were off by 30 to 60 microns consistently over repeated runs during two 

IRT entries. 

7.5.2 Droplet Splashing and Breakup

 Another hypothesis for the lower impingement efficiencies observed in the 

experimental investigation is droplet splashing and breakup which is discussed in some 

detail in Refs. 51–54. The basic assumption is that large droplets in the cloud, some 

considerably larger in diameter than the cloud MVD, deform upon impact and breakup 

into smaller droplets. The smaller droplets “bounce” forward (upstream) with some 

velocity and are carried downstream by the airflow. Thus, the amount of water that 

remains on the surface is considerably reduced. This hypothesis is also supported by 

experimental data obtained by other investigators during low speed large droplet 

impingement tests performed for engineering applications not related to aircraft icing as 

discussed in Refs. 52–54. The significance of this hypothesis, if proven true, is that 

trajectory and icing codes will have to be calibrated for large droplet impingement and 

ice accretion analyses. 

A. Studies at the Goodrich Icing Tunnel 

 Exploratory tests to investigate large droplet splashing and breakup were 

performed at the Goodrich Icing Tunnel in Uniontown, Ohio. Tests were conducted for 

warm (no ice) conditions and for various icing conditions. A Droplet Size and Velocity 

measuring device (Phase Doppler Particle AnalyzerPDPA) was used to measure 

droplet size and axial velocities near the leading edge of an airfoil for cases tested. The 

hypothesis was that if droplet breakup and splashing occurred, small droplets with 

negative axial velocities would have been present near the leading edge of the airfoil. 

 Figures 130–132 show the droplet and velocity distributions as well as the 

velocity versus droplet size at the leading edge of a 21-inch two-dimensional NACA0012 model. The tunnel airspeed, temperature, and MVD for the data presented in these 

figures were 175 mph, 31 °F and 104 μm respectively. In Fig. 131, a bimodal velocity 

distribution with a significant number of negative velocity counts is shown. In Fig. 132, 

small particles with negative velocities near the leading edge of the airfoil are evident. 

These observations, although not conclusive, support the hypothesis of large droplet 

splashing and breakup. 

B. Studies at the NASA Icing Research Tunnel 

 During the 1999 IRT impingement tests, a number of studies were conducted with 

the MS-0317 airfoil to investigate droplet splashing. Tests were conducted at different air 

speeds with a large droplet (MVD = 94 micron) cloud. The droplet impingement near the 

leading edge was visualized with a laser sheet normal to the span of the airfoil. A video 

camera was installed on the tunnel ceiling window with its lens set at a small angle with 

respect to the airfoil span and looking at the airfoil leading edge region near the midspan location. The speed of the tunnel was adjusted in increments of 25 mph from 50 to 

NASA/TM—2002-211700 56
200 mph and the region of impingement was videotaped. By increasing the speed of the 

airflow, the momentum of the particles was increased. When the air speed was 

increased beyond 100 mph, the region of impingement in the proximity of the leading 

edge exhibited significantly greater laser light scattering suggesting that the number of 

small particles was increased. The smaller particles present near the region of 

impingement were assumed to be the result of large droplet splashing. 

 

7.5.3 Future Work

 Tests are currently being planned to investigate large droplet splashing and 

breakup. These tests will include cloud and droplet impingement visualization methods 

to determine what happens to large droplets during impingement. 

	

			

An overview of previous impingement work was presented along with results from 

a recent industry survey indicating that a considerable expansion of the available 

impingement database was needed. A new impingement research program for providing 

the data requested by industry was outlined. The objectives of this program were to 

improve the experimental and data reduction methods for obtaining and reducing water 

droplet impingement data, and to perform extensive wind tunnel tests to expand the 

available impingement database. 

Significant improvements made to the experimental method developed by WSU 

and Boeing in the 1980’s and a new data reduction method for extracting the water 

droplet impingement data from the blotter strips were presented. An extensive 

discussion, supported by measurements performed, on known sources of error in the 

experimental and data reduction methods was provided. 

Extensive wind tunnel tests were conducted at the NASA Glenn Icing Research 

Tunnel to expand the water droplet impingement database and to provide large droplet 

impingement data. Tests were conducted with five single element airfoils; an airfoil with a 

simple flap, a high-lift system, three swept wings and an S-duct engine inlet. The single 

element airfoils had maximum thickness ratios in the range of 8% to 17% and were 

representative of sections used in general aviation and large commercial transport aircraft. 

Test conditions included freestream speeds in the range of 130 mph to 176 mph, a range 

of angles of attack and cloud median volumetric diameters of 11, 11.5, 21, 92 and 94 

micron. Each experimental condition for each test model was repeated 2 to 3 times and in 

some cases as many as 10 times to establish a measure of test repeatability. Additional 

tests were also performed to investigate the repeatability of spray system performance and 

its effect on LWC and droplet distribution. Comparisons of experimental and analysis 

impingement data obtained with the NASA Glenn LEWICE-2D and LEWICE-3D codes 

were performed. Below is a summary of key findings based on the work performed. 

NASA/TM—2002-211700 57
1. Automation of the WSU twelve nozzle spray system resulted in improved spray system 

performance. The WSU spray system with automated pressure feedback control was 

able to maintain air and water pressures at the spray nozzles to within 1 psi from the 

required settings. 

2. Repeated droplet distribution measurements showed that the variation in cloud MVD 

was ± 0.5 μm from the average for the 11.5 and 21-μm clouds and ± 2 μm from the 

average for the 92 and 94-μm clouds. 

3. A new method involving an Argon laser sheet and a CCD camera for determining cloud 

LWC uniformity was evaluated during this experimental investigation. Results from this 

new method were found to be in good correlation with the grid/blotter method 

developed previously. The laser sheet uniformity technique was considerably faster, 

less laborious and increased the resolution of the uniformity data compared to the grid 

and blotter method. 

4. A CCD reflectometer was developed for extracting the raw impingement data from the 

dye-laden blotter strips. The main advantage of the CCD system was its ability to 

reduce the experimental impingement data in a very short time allowing for on-line data 

reduction. This allowed for quick evaluation of the impingement data during the 1997 

and 1999 impingement experiments. The main drawbacks of the current CCD 

reflectometer design included difficulty in obtaining uniform blotter strip illumination, 

particularly for long strips, and decreased accuracy in regions where dye penetration 

into the blotter had occurred. 

5. The laser reflectometer was found to be more accurate than the CCD reflectometer in 

reducing the impingement data. This instrument allowed for a more uniform illumination 

of the blotter strip over the region of interest and was less sensitive to dye penetration 

into the blotter paper. The experimental impingement data presented in this report were 

reduced with the laser reflectometer. 

6. Relative humidity studies performed during the 1997 and 1999 IRT tests showed that 

the impact of relative humidity on LWC was considerable particularly for the 11 and 

11.5-μm spray clouds. 

7. The maximum difference of repeated impingement tests (3 to 10 repeats) from the 

average was in the range of 0.24% to 12% for approximately 85% of the test cases and 

13% to 17% for the remaining 15% of the test cases. This is a significant improvement 

in test repeatability compared to previous experimental investigations where variations 

in the range of 10% to 30% were observed in the experimental data. The number of 

repeats performed per test condition is not sufficient to establish a statistical average. 

However, the maximum differences recorded were consistent for the 500 impingement 

tests conducted to generate the experimental data presented in this paper. Thus, it 

would be reasonable to conclude that the experimental method used was repeatable. 

8. General impingement trends for the single element airfoils tested were as follows: 

a. For a fixed angle of attack, the total and maximum impingement efficiencies and the 

impingement limits increased with MVD as expected. 

b. In general, for a fixed MVD, the maximum impingement efficiency decreased with 

angle of attack. The total impingement efficiency, did not exhibit clear trends with 

angle of attack. For some models the total impingement efficiency increased as the 

angle of attack was increased. In other cases, however, the total impingement 

efficiency decreased as the angle of attack was increased. 

NASA/TM—2002-211700 58
c. In most cases, for the same MVD and angle of attack the thin airfoils (t/c = 8% to 

9%) resulted in higher maximum impingement efficiencies than the thicker airfoils 

(t/c = 14% to 17%). 

9. Impingement results for a 48-inch chord NLF-0414 airfoil with a 25% simple flap 

showed that for an angle of attack of 0 degrees, a flap deflection of 15 degrees trailing 

edge down did not have a significant effect on the magnitude of maximum and total 

impingement efficiencies compared to the nested flap case. However, for the flap 

deflection case, the extent of impingement along the lower surface of the airfoil 

increased considerably compared to the nested flap case. Water impingement was 

observed on the lower surface of the flap element in all cases and was found to extend 

all the way to the trailing edge. 

10. Experimental impingement data for the three-element high lift system tested, showed 

considerable impingement on the slat and flap elements. For α=0°, the impingement 

efficiency on the main element was less than 10% and extended all the way to the start 

of the cove. For α=4°, the impingement on the slat and flap was not significantly 

different than for the α=0°case. However, the magnitude of the maximum and total 

impingement on the main element was considerably increased at the higher angle of 

attack. For both angles of attack tested, impingement in the cove region of the main 

element was observed for the 11.5 and 21-micron cases only For both angles of attack, 

impingement along the flap lower surface extended to the trailing edge of the flap. 

11. For the three swept tail configurations tested, the experimental and analysis 

impingement data presented showed little variation with spanwise location. Water 

impingement was increased as the MVD size of the cloud was increased. In addition, 

the impingement region was shifted towards the pressure side of the wing as the angle 

of attack was increased. The extent of water impingement was considerably greater at 

the higher angles of attack. 

12. Impingement scaling experiments conducted with 36-inch and 48-inch chord NLF-0414 

airfoils and with a full-scale and a 25%-scale business jet swept tails showed that for 

the same air speed, angle of attack and MVD size the smaller scale models resulted in 

higher impingement efficiencies. The chordwise extent of impingement was also 

greater for the smaller scale models. 

13. Experimental impingement data for the S-Duct engine inlet showed considerable 

impingement along the engine outer lip, the splitter nose dividing the engine flow from 

the scavenge flow, and along the lower surface of the torque tube located in the engine 

flow duct. Some impingement was also observed along the interior sidewall of the main 

inlet duct for the 21 and 94-micron MVD cases. In general, the impingement intensity at 

all inlet locations tested increased as the droplet size was increased from 11 to 94 

microns. For each MVD case, total and maximum impingement efficiencies at stations 

C and D corresponding to the apex corner and lower surface of the torque tube, 

increased as the inlet capture area ratio was increased. 

14. In general, good agreement between the experimental results and analysis data 

obtained with the NASA Glenn LEWICE-2D and LEWICE-3D computer codes was 

demonstrated for the 11, 11.5 and 21-micron cases. However, for the 92 and 94-micron 

cases the analysis produced considerably higher overall impingement than the 

experiment for nine out of the eleven models tested and for all angles of attack. 

NASA/TM—2002-211700 59
15. Exploratory tests conducted with the 94-micron spray cloud and with various test 

models suggest that droplet splashing may be the main reason for the discrepancy 

observed between the experimental and the LEWICE data. These preliminary findings 

are supported by recent research efforts in large droplet impingement performed for 

engineering applications unrelated to aircraft icing. More research is needed to further 

explore phenomena associated with large droplet impingement for icing applications. 

 

NASA/TM—2002-211700 60
Table 1 Test geometries and conditions for NACA impingement tests (1955-1958). 

NACA 

TN # 

Geometry MVD 

 (μm) 

α 

(deg.) 

V∞ 

(mph) 

3338 Cylinders (Diam. = 2,4 and 6 inches,

Span = 1 ft) 

7.6, 12, 14.8 0 175 

4092 Spheres (Diam. 5.92, 18 inch) 11.5, 12.7, 

16.7-18.6 

0 181 

4092 Ellipsoids (minor axis 30 and 20 

inch ) with fineness ratios of 2.5 and 

3.0 

11.5, 12.7, 

16.7-18.6 

0, 3, 6 181 

4092 Conical (30°) with 18.93 inch base 

radius- RPMs = 0, 600, 800, 1200 

11.5, 12.7, 

16.7-18.6 

0, 3, 6 181 

3564 NACA 0011, 87 inch chord, 6 foot 

span 

22-59 0 to 9.3 175 - 275 

3839 Joukowski 0015, NACA: 651-206, 

652-206, 651-212, 652-212, 632-015, 

652-216 

chord lengths: 13-96 inches 

11.5, 16.7, 

18.6 

0 to 12 175 

4151 NACA 65A004 (unswept) 

19 inch cord, 42 inch span 

 11 275 

4155 NACA 65A004, 6 ft chord, 42 inch 

span removable L.E., flap angle: 

-15° to 15°

11-19 0 to 12 125 - 276 

4268 Supersonic inlet with – conical 

center body 

11.5, 16.7, 

19.4 

0 to 4.2 179 

Table 2 Test matrix for 1985 impingement tests (all tests were conducted 

at a freestream speed of 165 mph, each test condition 

was repeated 2-3 times, Ref. 6). 

Geometry MVD 

 (μm) 

α 

(deg.) 

Mass Flow

(lbm/sec) 

Cylinder (2, 4 inches in diameter) 16.5, 20.4 0 NA 

NACA 652-015 airfoil (13 inch chord) 16.5, 20.4 0, 8 NA 

MS(1)-0317 airfoil (36 inch chord) 16.5, 20.4 0, 8 NA 

Rime Ice Shape 20.4 0 NA 

Small Glaze Ice Shape on 2-in 

diameter cylinder 

20.4 0 NA 

Large Glaze Ice Shape on 2-in 

diameter cylinder 

20.4 0 NA 

Axisymmetric Engine Inlet 16.5, 20.4 0, 15 17, 23 

Boeing 737-300 Engine Inlet 16.5, 20.4 0, 15 17, 23 

NASA/TM—2002-211700 61
Table 3 Test matrix for 1989 impingement tests (all tests were conducted at a 

freestream speed of 165-173 mph, each test condition 

 was repeated 5 times, Ref. 7). 

Geometry MVD 

(μm) 

α 

(deg.) 

Mass Flow

(lbm/sec) 

Small Glaze Ice Shape on 2-in diameter 

cylinder 

20.4 0 NA 

Large Glaze Ice Shape on 2-in diameter 

cylinder 

20.4 0 NA 

NLF(1)-0414F airfoil (36 inch chord) 16.5, 20.4 0, 8 NA 

MS(1)-0317 airfoil, 30 deg. infinite swept 

Wing ( 36 inch chord) 

16.5, 20.4 0, 8 NA 

NACA 0012, 30 deg. swept finite wing, 

(15 inch chord) 

16.5, 20.4 0, 8 NA 

Boeing 737-300 Engine Inlet 16.5, 20.4 0, 15 17, 23 

Table 4 Survey participants by company. 

AIRCRAFT COMPANIES ENGINE AND INLET COMPANIES 

Boeing Commercial Airplane Group - 

Seattle (8) 

Allison Engine Company (2) 

Boeing Commercial Airplane Group – 

Wichita Division (1) 

GE Aircraft Engines (1) 

Douglas Products Division -Long Beach (1) Rohr, Inc. (1) 

Lockheed Martin Aeronautical Systems (1) OTHER COMPANIES 

Cessna Aerospace Corporation (2) AlliedSignal Aerospace (1) 

Gulfstream Aerospace Corporation (1) Chrysler Technologies Airborne Systems (2) 

Learjet, Inc. (2) Key Industries Corporation (1) 

The New Piper Aircraft, Inc. (1) FAA/UNIVERSITIES 

HELICOPTER COMPANIES FAA Technical Center - Atlantic City (1) 

Bell Helicopter Textron, Inc. (1) Univ. of Illinois at Urbana-Champaign (1) 

Sikorsky Aircraft Corporation (1) 

The number in parentheses shows number of respondents 

NASA/TM—2002-211700 62
Table 5 Geometry requested by group. 

ORGANIZATION AIRFOIL 

SECTIONS 

WINGS TAILS INLETS 

S-DUCTS 

PROPS OTHER 

Large Aircraft Manufacturers 

3/5/2 4/1/0/D 1/HV 2/0/1/2c 

Business Jet Manufacturers 

1/2/1 3/0/1 2 I 

Small Aircraft Manufacturers 

 5/0/0 1 1/0/1 

Helicopter Companies 3/1/1 Aircraft Engine/Inlet Comp. 

 5/4/1/1c II 

Military Aircraft Companies 

 1/0/1 

FAA 1/2/0 2/0/0 1 Universities 1/2/0 1 Other 1/0/1 1/1/1 III Total (Approx. 80 models) 

10/12/5 14/1/1/D 5/HV 10/5/5/3c 1 

Airfoil Sections: Single/Multi-element/With Ice Shapes; Wings: Single/Multi-element/With Ice Shapes/Delta Wings; Tails: HV - Horizontal & Vertical; Inlets S-Ducts: Inlet/S-duct/With Ice Shapes/Cascade 

Configurations; I - Windshields, II - Spinners, Center bodies, III - Radomes, Antennas, Appendages. 

NASA/TM—2002-211700 63
Table 6 List of droplet trajectory parameters. 

Parameter Definition Expression 

ReMVD Reynolds number based on droplet 

diameter μ

ρ air V MVD ⋅ ⋅ ∞ where MVD represents Median Volumetric 

Diameter, ρair is the air density and μ is the absolute air viscosity 

K Droplet inertia parameter c

MVD

18

V

2

droplet

⋅ ⋅

⋅ ⋅

∞

μ

ρ where ρdroplet is the droplet (water) density and c

is the chord length of the airfoil model 

s

λ

λ

Ratio of the true range of droplet as projectile injected into still air to the range of droplet as projectile following Stokes’ law 

74544 . 0 x 36072 . 0 x 59067 . 0 x 20109 . 0 x 022466 . 0 2 3 4 + ⋅ + ⋅ − ⋅ + ⋅ −

where x = log(ReMVD) and 6 < ReMVD < 1000

K0 Droplet modified inertia parameter 

s

K λλ⋅

φ Deviation of the droplet drag force from Stokes’ law ( ) K Re 2 MVD

ψ φK

NASA/TM—2002-211700 64
Table 7 Pressure taps for 48-in NLF(1)-0414 airfoil. 

Table 8 Pressure taps for three-element high lift system airfoil. 

Element Chordwise Taps Spanwise Taps Upper Surface 

Slat 35 6 (row near LE) 

Main 42 NA 

Flap 33 6 (row near LE) 

6 (row near TE) 

Table 9 Summary of pressure transducer characteristics. 

Transducer Usage Range 

(psig) 

Error Thermal 

Zero shift Error 

Thermal 

Span shift Error 

13 SETRA 206 Water lines 0-125 ±0.13% FS ±1.0% FS/100°F ±1.5% FS/100°F 1 SETRA 204 Main air line 0-100 ±0.11% FS ±0.4% FS/100°F ±0.3% FS/100°F 3 SETRA 206 Nozzle air lines 0-100 ±0.13% FS ±1.0% FS/100°F ±1.5% FS/100°F 

Note: all transducers were calibrated at temperature of 50°F 

Element Chordwise Taps Spanwise Taps Main 58 taps at 33 inches above floor 12 taps (x/c=0.725) at 6 inch increments. 

3 taps overlapping with chordwise ports. 

7 taps 43 inches above floor Main 

7 taps 23 inches above floor 

Control 43 taps 33 inches above floor 

NASA/TM—2002-211700 65
Table 10a Cloud MVD and corresponding spray system parameters from test measurements (1997 IRT tests). 

FSSP+OAP 

MVD 

Range 

(μm) 

Average 

Air Supply 

Pressure 

At Regulator 

(psig 

± psi) 

Average 

Tank Water 

Pressure 

(psig 

± psi) 

Average 

Water Pressure 

At Nozzle 

(psig 

± psi) 

Average Air Pressure At 

Nozzle 

(psig 

± psi) 

∆P = 

Pwater-Pair

At Nozzle 

(psi) 

Average 

Volume Flow 

Rate 

12 Nozzles 

(GPM) 

Spray 

Time (sec) 

11.5 45.5 

± 0.6 68.0 

± 1.0 61.5 

± 1.0 40 

± 0.6 21.5 0.190 18 

21 24.5 

± 0.9 76.5 

± 0.8 69.5 

± 0.8 21 

± 0.8 48.5 0.275 6 

92 6.0 

± 0.3 40.5 

± 0.6 34.5 

± 0.6 4.5 

± 0.3 30.0 0.205 3 

Pressures, flow rates and errors have been calculated from 100 randomly selected tests for each MVD case. 

Table 10b Cloud MVD and corresponding spray system parameters from test measurements (1999 IRT tests). 

FSSP+OAP 

MVD 

Range 

(μm) 

Average 

Air Supply 

Pressure 

At Regulator 

(psig 

± psi) 

Average 

Tank Water 

Pressure 

(psig 

± psi) 

Average 

Water Pressure 

At Nozzle 

(psig 

± psi) 

Average Air Pressure At 

Nozzle 

(psig 

± psi) 

∆P = 

Pwater-Pair

At Nozzle 

(psi) 

Average 

Volume Flow 

Rate 

12 Nozzles 

(GPM) 

Spray 

Time (sec) 

11 43.0 

± 0.7 67.0 

± 0.4 62.8 

± 0.5 38.2 

± 0.4 24.6 0.226 9.0 

21 22.0 

± 0.4 77.0 

± 0.4 72.5 

± 0.5 18.9 

± 0.4 53.6 0.329 3.8 

92 6.0 

± 0.6 37.0 

± 0.4 32.4 

± 0.5 4.7 

± 0.5 27.2 0.185 2.2 

Pressures, flow rates and errors have been calculated from 45 randomly selected tests for each MVD case. 

NASA/TM—2002-211700 66
Table 11 Collector theoretical efficiency and King probe LWC measurements 

for 1997 and 1999 test MVDs. 

Year MVD Range (FSSP+OAP) 

(μm) 

Average MVD 

(μm) 

Average LWC1,2 

(g/m3) Collector Efficiency (%) 

11-12 11.5 0.04 82 20-22 21 0.15 89 1997 90-94 92 0.22 97 11-12 11 0.05 82 20-22 21 0.19 89 1999 90-94 94 0.22 97 

1. 1997 LWC King Probe data were obtained at the center of the tunnel test section (relative 

humidity ranged from 70% to 80%). IRT spray bar air was used to enhance cloud uniformity. 

2. 1999 King Probe LWC data were obtained at the center of the tunnel test section (relative 

humidity ranged from 70% to 75%). IRT spray bar air was not used. Automatic feedback was used to control air and water pressures. 

NASA/TM—2002-211700 67
Table 12a Test models and conditions (1997 Impingement tests). 

Test Model 

Number of 

Surface 

Pressure Taps 

Angle of Attack (

α) 

Flap deflection (

δ) 

(degrees) 

MVD 

(μm) 

Average 

Air 

Speed 

Number of 

Runs per 

MVD 

Total 

Number 

of Runs 

MS(1)-0317 (c = 36 in) Strip Location: Midspan 

49 

α = 0, 8 11.5, 21, 92 176 mph 4 24 

NACA 652-415 (c = 36 in) Strip Location: Midspan 

100 

α = 0, 8 11.5, 21, 92 176 mph 4 to 11 53 

Commercial transport tail section (c = 36 in) Strip Location: Midspan 

44 

α = 0, 4 11.5, 21, 92 176 mph 4-10 19 

GLC 305 (c = 36 in) Strip Location: Midspan 

44 

α = 1.5, 6 11.5, 21, 92 176 mph 4 24 

NACA 64A008 tail (ΛLE = 29.1°, ΛTE = 11.1°, 

cr = 45.48 in, ct = 28.16 in) 

See figure 14d for locations 

60 

α = 0, 6 11.5, 21, 92 176 mph 4 24 

Three-element high lift system airfoil (36 in nested chord) Strip Location: Midspan 

128 

α = 0, 4 δ = Landing Configuration 

11.5, 21, 92 176 mph 4 24 

Collector Mechanism NA 

α = 0, 3 locations 11.5, 21, 92 176 mph 4 to 6 133 

Uniformity 6ft x 6ft Grid NA NA 11.5, 21, 92 175 mph 43 140 MVD, LWC measurements NA NA 10-130 176 mph 2-4 53 Humidity studies, Blotter penetration tests, Other 

NA NA 11.5, 21, 92 176 mph 1-3 24 

NASA/TM—2002-211700 68
Table 12b Test models and conditions (1999 impingement tests). 

Test Model 

Number of 

Surface 

Pressure Taps 

Angle of Attack (

α) 

Flap deflection (

δ) 

(degrees) 

MVD 

(μm) 

True Air Speed 

& Inlet Mass 

Flow 

Number 

of Runs 

per MVD 

Total 

Number 

of Runs 

MS(1)-0317 (c = 36 in) Strip Location: Midspan 

49 

α = 0 11, 21, 94 176 mph 3 9 

NLF(1)-0414 (c = 36 in) Strip Location: Midspan 

5 

α = 0, 8 11, 21, 94 176 mph 3 21 

NLF(1)-0414 (c = 48 in) Strip Location: Midspan 

124 

α = 0, 4, 8 δ = 0 

11, 21, 94 175 mph 3 to 4 46 

NLF(1)-0414 (c = 48 in) Strip Location: Midspan 

124 

α = 0 δ = 15 

11, 21, 94 175 mph 3 to 4 46 

25%-scale Business Jet Empennage See figure 15e for location. 

126 

α = 1, 6 δ = 0 

11, 21, 94 176 mph 3 21 

Full-scale Business Jet Tail Section See figure 16e for locations 

NA 

α = 1, 2, 6 δ = 0, 3 

11, 21, 94 176 mph 3 18 

130 mph 

MIF= 23 lb/s 

SF = 1.57 lb/s 

CAR = 0.84 

S-duct Engine Inlet See figure 22h for blotter strip locations 

30 NA 11, 21, 94 

170 mph 

MIF = 23 lb/s 

SF = 2.08 lb/s 

CAR = 0.65 

2-3 17 

Collector Mechanism NA 

α = 0 (3 locations) 11, 21, 94 175 – 176mph 1 to 6 54 

Uniformity Test (include 6ft x 6ft grid and laser sheet technique) 

NA NA 11, 21, 94 170 – 177 mph 1 to 24 176 

MVD, LWC measurements NA NA 11, 21, 94 175 – 176 mph 3 to 4 67 Humidity studies, Droplet break-up tests, Blotter penetration tests, Other 

NA NA 11, 21, 94, 

270 

40 – 200 mph 1 to 3 46 

1. MIF = Main Inlet Flow 2. SF = Scavenge Flow 3. CAR = Capture Area Ratio

NASA/TM—2002-211700 69
Table 13 Summary of model geometry and impingement parameters (All dimensions are in 

English Units (inch, mph); Values inside parenthesis are in SI Units (meter, m/s) (Continued). 

Geometry Chord tmax x/c at 

V

∞ Rec AOA MVD ReMVD K K0 φ

(test year) (in) (in) tmax mph Million (deg.) (μm) 

11.5 60 0.036 0.015 21.0 110 0.119 0.041 0.0 92.0 483 2.286 0.413 11.5 60 0.036 0.015 21.0 110 0.119 0.041 

MS(1)-0317 

(1997 & 1999)

36 

(0.914) 

6.12 

(0.155) 

0.376 176 

(78.66) 

4.83 

8.0 

92.0 483 2.286 0.413 

101,845 

11.5 60 0.036 0.015 21.0 110 0.119 0.041 1.5 92.0 483 2.286 0.413 11.5 60 0.036 0.015 21.0 110 0.119 0.041 

GLC-305 

(1997) 

36 

(0.914) 

3.12 

(0.079) 

0.398 176 

(78.66) 

4.83 

6.0 

92.0 483 2.286 0.413 

101,846 

11.5 60 0.035 0.015 21.0 110 0.117 0.040 0.0 92.0 483 2.253 0.407 11.5 60 0.035 0.015 21.0 110 0.117 0.040 

NACA 

652-415 

(1997) 

36.53 

(0.928) 

5.49 

(0.139) 

0.402 176 

(78.66) 

4.85 

8.0 

92.0 483 2.253 0.407 

103,345 

11.5 60 0.036 0.015 21.0 110 0.119 0.041 0.0 92.0 483 2.286 0.413 11.5 60 0.036 0.015 21.0 110 0.119 0.041 

Commercial 

transport tail 

section 

(1997) 

36 

(0.914) 

3.23 

(0.082) 

0.338 176 

(78.66) 

4.84 

4.0 

92.0 483 2.286 0.413 

101,846 

NASA/TM—2002-211700 70
Table 13 Summary of model geometry and impingement parameters (All dimensions are in English Units (inch, mph); 

Values inside parenthesis are in SI Units (meter, m/s) (Continued).

Geometry Chord tmax x/c at 

V

∞ Rec AOA MVD ReMVD K K0 φ

(test year) (in) (in) tmax mph Million (deg.) (μm) 

11.0 58 0.033 0.014 21.0 110 0.119 0.041 0.0 94.0 493 2.386 0.427 11.0 58 0.033 0.014 21.0 110 0.119 0.041 

36-inch 

NLF(1)-0414 

(1999) 

36 

(0.914) 

5.14 

(0.131) 

0.467+ 176 

(78.66) 

4.84 

8.0 

94.0 493 2.386 0.427 

101,846 

11.0 58 0.025 0.011 21.0 110 0.089 0.030 0.0 94.0 493 1.790 0.320 11.0 58 0.025 0.011 21.0 110 0.089 0.030 4.0 94.0 493 1.790 0.320 11.0 58 0.025 0.011 21.0 110 0.089 0.030 

48-inch 

NLF(1)-0414 

(with 25% 

chord flap) 

(1999) 

48 

(1.219) 

6.85 

(0.1744) 

0.467+ 175 

(78.22) 

6.53 

8.0 

94.0 493 1.790 0.320 

135,794 

11.5 60 0.034* 0.014*21.0 110 0.114* 0.039* 0.0 92.0 483 2.186* 0.395*11.5 60 0.034* 0.014*21.0 110 0.114* 0.039*

NACA 

64A008 

Swept finite 

 span tail 

(1997) 

37.65* 

(0.956*)

3.01* 

(0.077*)

0.39 176 

(78.66) 

5.03*

6.0 

92.0 483 2.186* 0.395*

106,514*

NASA/TM—2002-211700 71
Table 13 Summary of model geometry and impingement parameters (All dimensions are in English Units (inch, mph); 

Values inside parenthesis are in SI Units (meter, m/s)

Geometry Chord tmax x/c at 

V

∞ Rec AOA MVD ReMVD K K0 φ

(test year) (in) (in) tmax mph Million (deg.) (μm) 

11.0 58 0.105 0.045 21.0 110 0.383 0.130 -1.0 94.0 494 7.671 1.371 11.

0 58

0.105

0.0

4

5

21.0 110 0.383 0.130 

25%-scale 

Business jet 

empennage 

(1999) 

12.31* 

(0.313*)

0.9* 0.39 176 

(78.66) 

1.493*

-6.0 

94.0 494 7.671 1.371 

31,764* 

11.0 58 0.034 0.015 21.0 111 0.123 0.042 1.0 94.0 496 2.463 0.440 

Full-scale 

Business jet 

tail section 

(1999) 

32.18* 

(0.82) 

2.57* 

(0.065) 

0.39 176 

(78.66) 

4.312* 

6.0 21.0 111 0.123 0.042 

99,824* 

* Data based on MAC; + Average value

NASA/TM—2002-211700 72
Table 14 Effect of relative humidity on droplet distribution and LWC 

(FSSP measurements) – MVD = 11-12 

μm. 

. 

Droplet Size 

(μm) 

Droplet Counts 

(60% Relative 

Humidity) 

Droplet Counts 

(70% Relative 

Humidity) 

Droplet Counts 

(70% Relative 

Humidity) 

Droplet Counts 

(80% Relative 

Humidity) 

3.5 875.84 1202.65 1306.98 2702.63 6.5 781.12 1151.86 1208.51 1984.2 9.5 571.82 821.65 888.41 1464.71 

12.5 186.71 223.73 254.35 468.61 15.5 67.22 74.92 85.43 158.39 18.5 31.63 29.27 34.55 64.98 21.5 10.69 6.51 8.35 16.55 24.5 2.31 1 1.39 2.63 27.5 0.2 0.06 0.12 0.1 30.5 0 0.04 0.02 0.06 

MVD (

μm) 12 11 11 11.3 

LWC (g/m3

) 0.030 0.044 0.049 0.098 

NASA/TM—2002-211700 73
Table 15 Summary of test repeatability results. 

Test Case AOA 

deg 

MVD = 11, 11.5 

μm 

MVD = 21 

μm 

MVD =92, 94 

μm 

MS(1)-0317 (1997) 0 ±12% ± 3% ± 9.1% 

MS(1)-0317 (1997) 8 ± 8.8% ± 7.1% ± 3.6% 

MS(1)-0317 (1999) 0 ± 5.7% ± 3.1% ± 11% 

GLC-305 (1997) 1.5 ± 8.7% ± 8.8% ± 8.7% 

GLC-305 (1997) 6 ± 16% ± 6% ± 4.9% 

NACA 652-415 (1997) 0 ± 14% ± 8.1% ± 7% 

NACA 652-415 (1997) 8 ± 13% ± 11% ± 17% 

Transport Tail (1997) 0 ± 9.6% ± 4.8% ± 9.2% 

Transport Tail (1997) 4 ± 1.7% ± 7% ± 9.8% 

NLF-0414 36-in (1999) 0 ± 5.3% ± 0.24% ± 14% 

NLF-0414 36-in (1999) 8 ± 3.8% ± 2.3% ± 11% 

NLF-0414f 48-in (1999) δ=0 0 ± 2.9% ± 7.3% ± 8.1% 

NLF-0414f 48-in (1999) δ=0 4 ± 4.6% ± 8% ± 0.8% 

NLF-0414f 48-in (1999) δ=0 8 ± 3.8% ± 9.7% ± 6.2% 

NLF-0414f 48-in (1999)δ=15 0 ± 5.9% ± 7.9% ± 11% 

NACA 64A008 (1997) 0 ± 4.9% ± 7.4% ± 3.9% 

NACA 64A008 (1997) 6 ± 12% ± 8.2% ± 3.2% 

25%-Scale BJE (1999) Inboard -1 ± 4% ± 6.2% ± 5.9% 

25%-Scale BJE (1999) Inboard -6 ± 4.9% ± 5.7% ± 7.1% 

25%-Scale BJE (1999) Outboard -1 ± 4.8% ± 14% ± 3.7% 

25%-Scale BJE (1999) Outboard -6 ± 3.4% ± 4.6% ± 3.2% 

BJ Horizontal Tail (1999) Inboard 1 ± 4.4% ± 1.9% ± 8.5% 

BJ Horizontal Tail (1999) Inboard 6 - ± 8.7% - 

BJ Horizontal Tail (1999) Outboard 1 ± 1.6% ± 2.4% ± 8.2% 

BJ Horizontal Tail (1999)Outboard 6 - ± 6.7% - 

High Lift System (1997) Slat 0 ±7.7% ±11% ±9.2% 

High Lift System (1997) Main 0 ±17% ±17% - 

High Lift System (1997) Flap 0 ±10% ±10% ±8.6% 

High Lift System (1997) Slat 4 ±11% ±9.4% ±16% 

High Lift System (1997) Main 4 ±11% ±5.6% ±9.5% 

High Lift System (1997) Flap 4 ±7.5% ±8.5% ±15% 

S-Duct Inlet car=0.6 A 0 ±6.8% ±4.6% ±11% 

S-Duct Inlet car=0.6 B 0 - ±13% ±12% 

NASA/TM—2002-211700 74
Table 16 Summary of impingement efficiency data for both 1997 and 1999 IRT tests (Continued).

Model Test Conditions 

βmax max

Sβ Su Sl xu/c xl/c 

β

A f A

E

(Test Year) 

α MVD 

δ (mm) (mm) (mm) (mm) (mm) 

11.5 NA 0.32 -6 -71 30 0.048 0.016 11.09 155.50 0.0713 21.0 NA 0.50 -1 -90 45 0.068 0.031 26.43 155.50 0.1699 0 92.0 NA 0.68 -4 -240 149 0.229 0.142 49.53 155.50 0.3186 11.5 NA 0.25 +16 -15 66 0.004 0.053 7.690 186.91 0.0411 21.0 NA 0.51 +12 -34 185 0.016 0.181 33.43 186.91 0.1788 

MS(1)-0317 

(1997) 

8.0 

92.0 NA 0.76 +8 -60 300 0.038 0.307 67.41 186.91 0.3607 

11.0 NA 0.33 -6 -62 30 0.048 0.016 12.08 155.50 0.0777 21.0 NA 0.50 0 -89 63 0.078 0.047 29.84 155.50 0.1919 

MS(1)-0317 

(1999) 0 

94.0 NA 0.68 -2 -164 117 0.147 0.107 50.17 155.50 0.3224 

11.5 NA 0.47 +1 -26 34 0.017 0.041 9.248 79.321 0.1166 21.0 NA 0.66 +2 -42 55 0.026 0.069 16.34 79.321 0.2060 1.5 92.0 NA 0.76 +2 -153‡ 229‡ 0.145 0.264 26.08 79.321 0.3288 11.5 NA 0.43 +6 -14 60 0.007 0.075 8.956 115.18 0.0778 21.0 NA 0.60 +6 -22 322 0.015 0.365 25.81 115.18 0.2241 

GLC-305 

(1997) 

6.0 

92.0 NA 0.72 +4 -25 526‡ 0.168 0.588 46.75 115.18 0.4059 

11.5 NA 0.45 +1 -48 40 0.037 0.035 8.255 139.34 0.0592 21.0 NA 0.62 0 -140 75 0.132 0.072 19.51 139.34 0.1400 0 92.0 NA 0.73 -2 -195 150 0.192 0.200 36.48 139.34 0.2618 11.5 NA 0.30 +11 -15 135 0.005 0.136 7.896 175.83 0.0449 21.0 NA 0.52 +11 -20 227 0.010 0.234 22.04 175.83 0.1254 

NACA 652-415 

(1997) 

8.0 

92.0 NA 0.69 +8 -100‡ 407‡ 0.090 0.556 61.63 175.83 0.3505 11.5 NA 0.47 -1 -41 25 0.038 0.016 9.051 82.035 0.1103 21.0 NA 0.60 -1 -82 52 0.082 0.043 17.76 82.035 0.2165 0 92.0 NA 0.76 -1 -130 100 0.135 0.094 29.81 82.035 0.3634 11.5 NA 0.41 +4 -23 55 0.019 0.046 8.959 98.976 0.0905 21.0 NA 0.54 +4 -40 175 0.037 0.176 19.03 98.976 0.1923 

Commercial 

transport tail 

section 

(1997) 4.0 

92.0 NA 0.74 +2 -80 371‡ 0.080 0.390 42.06 98.976 0.4249 

NASA/TM—2002-211700 75
Table 16 Summary of impingement efficiency data for both 1997 and 1999 IRT tests (Continued). 

Model Test Conditions 

βmax max

Sβ Su Sl xu/c xl/c 

β

A f A

E

(Test Year) 

α MVD 

δ (mm) (mm) (mm) (mm) (mm) 

11.0 NA 0.45 -3 -35 33 0.023 0.028 9.705 130.48 0.0744 21.0 NA 0.60 -2 -76 79 0.065 0.077 20.45 130.48 0.1567 0 94.0 NA 0.77 -2 -230** 180 0.231 0.187 35.26 130.48 0.2702 11.0 NA 0.37 +5 -22 100 0.011 0.010 10.79 189.49 0.0569 21.0 NA 0.57 +8 -20 400 0.009 0.427 36.85 189.49 0.1945 

36-inch 

NLF(1)-0414 

(1999) 8.0 

94.0 NA 0.75 +8 -30 465** 0.018 0.498 61.48 189.49 0.3244 11.0 0 0.40 -2 -35 45 0.015 0.029 10.32 173.97 0.0593 21.0 0 0.55 -2 -95 84 0.060 0.060 22.81 173.97 0.1312 0 94.0 0 0.75 -2 -200 180 0.144 0.138 44.98 173.97 0.2586 11.0 0 0.38 +10 -25 65 0.008 0.045 10.19 193.66 0.0526 21.0 0 0.52 +8 -40 340 0.018 0.268 31.46 193.66 0.1624 4.0 94.0 0 0.72 +7 -60 446 0.033 0.355 55.71 193.66 0.2877 11.0 0 0.36 +16 -10 98 0.001 0.071 11.22 252.65 0.0444 21.0 0 0.51 +11 -28 370 0.010 0.293 36.87 252.65 0.1459 8.0 94.0 0 0.70 +7 -42 750 0.020 0.604 78.30 252.65 0.3099 11.0 15 0.41 +7 -33* 70* 0.013 0.049 12.13* 212.09 0.0572* 21.0 15 0.55 +8 -50* 180* 0.026 0.138 27.29* 212.09 0.1287* 

48-inch 

NLF(1)-0414 

with 25%- 

chord flap 

(1999) 

0 

94.0 15 0.75 +6 -110* 300* 0.072 0.236 51.81* 212.09 0.2443* 11.5 NA 0.45 0 -25 25 0.023 0.022 5.974 76.514 0.0781 21.0 NA 0.61 +2 -80 80 0.082 0.082 13.86 76.514 0.1811 0 92.0 NA 0.71 0 -180 180 0.191 0.190 23.08 76.514 0.3016 11.5 NA 0.45 +6 -5 80 0.017 0.082 8.789 116.07 0.0757 21.0 NA 0.61 +5 -10 310 0.020 0.332 26.23 116.07 0.2260 

NACA 64A008 

Swept finite 

span tail 

(1997) 6.0 

92.0 NA 0.70 +3 -20 400‡ 0.018 0.431 41.69 116.07 0.3592 

NASA/TM—2002-211700 76
Table 16 Summary of impingement efficiency data for both 1997 and 1999 IRT tests. 

Model Test Conditions 

βmax 

max

Sβ Su Sl xu/c xl/c 

β

A f A

E

(Test Year) 

α MVD 

δ (mm) (mm) (mm) (mm) (mm) 

11.0 0 0.60 0 -20s 20p 0.049s 0.050p 7.467 29.037 0.2571 21.0 0 0.70 0 -40s 50p 0.105s 0.134p 11.74 29.037 0.4043 -1.0 

94.0 0 0.80 +1 -40s 50p 0.105s 0.134p 13.33 29.037 0.4592 

11.0 0 0.59 +3 -10s 80p 0.022s 0.219p 10.13 45.292 0.2237 21.0 0 0.68 +3 -15s 150p 0.036s 0.416p 15.42 45.292 0.3405 

25%-scale 

Business jet 

empennage 

(1999) 

<Inboard> -6.0 

94.0 0 0.77 +3 -20s 150p 0.049s 0.416p 15.94 45.292 0.3519 

11.0 0 0.62 0 -20s 25p 0.063s 0.082p 6.794 23.242 0.2923 21.0 0 0.73 0 -35s 40p 0.119s 0.131p 11.87 23.242 0.5106 -1.0 

94.0 0 0.81 +1 -40s 45p 0.133s 0.152p 13.03 23.242 0.5606 

11.0 0 0.62 +2 -10s 70p 0.029s 0.240p 10.27 36.253 0.2833 21.0 0 0.71 +3 -15s 150p 0.046s 0.521p 17.48 36.253 0.4822 

25%-scale 

Business jet 

empennage 

(1999) 

<Outboard> -6.0 

94.0 0 0.77 +2 -20s 150p 0.063s 0.521p 13.19 36.253 0.3638 

11.0 0 0.44 -1 -35 30 0.033 0.028 7.714 71.202 0.1083 21.0 0 0.58 0 -70 45 0.071 0.045 16.30 71.202 0.2289 1.0 

94.0 0 0.72 -1 -120 110‡ 0.127 0.118 21.21 71.202 0.2979 

Full-scale 

business jet 

horizontal tail 

(1999) 

<Inboard> 

6.0 21.0 0 0.57 +5 -35 305 0.033 0.344 18.57 118.88 0.1562 

11.0 0 0.46 0 -35 30 0.036 0.031 8.661 65.682 0.1319 21.0 0 0.61 -1 -70 45 0.078 0.049 15.87 65.682 0.2417 1.0 

94.0 0 0.75 0 -120 110 0.139 0.128 23.66 65.682 0.3602 

Full-scale 

business jet 

horizontal tail 

(1999) 

<Outboard> 

6.0 21.0 0 0.61 +3 -35 305 0.036 0.373 22.78 122.82 0.1855 

Nomenclature for Table 16 1. 

max β S represents the surface distance from the reference point to the location of the maximum impingement efficiency. 

Su and 

Sl represent the surface 

distances of impingement limits on the upper and lower surfaces. xu/c and xl/c represent the stations of the impingement limits on upper and lower surfaces 

with respect to the chord. 

2. 

β

A represents the total area under the local impingement efficiency curve, which is defined as 

∫ ds

β ; where ds is the infinitesimal surface distance. 

3. f A represents the projected frontal area of the airfoil. 

4. 

E represents the total impingement efficiency, which is defined as 

f

A

A

E

β

=

5. * impingement characteristics on the main-element only, do not include the flap-element (for 48 in NLF(1)-0414 airfoil) 6. ‡ end of blotter strip 7. s = suction surface, p = pressure surface 

NASA/TM—2002-211700 77
Table 17 Summary of impingement efficiency data for three-element high lift system. 

Element Test Condition 

βmax 

max

Sβ Su Sl xu/c xl/c 

β

A f A

E

(test year) 

α MVD 

δ (mm) (mm) (mm) (mm) (mm) 

11.5 30 0.35 -5 -71 15 -0.048 -0.080 9.294 231.42 0.0402 21.0 30 0.60 -7 -142++ 20 0.001 -0.076 27.46 231.42 0.1187 0 

92.0 30 0.84 -7 -142++ 25 0.001 -0.072 60.23 231.42 0.2603 

11.5 30 0.35 +2 -35 30 -0.071 -0.067 7.696 292.45 0.0263 21.0 30 0.64 +2 -142++ 37 0.001 -0.061 22.12 292.45 0.0756 

Leading Edge 

Slat 

(1997) 4.0 

92.0 30 0.82 +1 -142++ 40 0.001 -0.058 43.62 292.45 0.1492 

11.5 NA 0.05 +35 0 110 0 0.134 1.459 231.42 0.0063 21.0 NA 0.04 +21 0 275 0 0.281 4.763 231.42 0.0206 

0 

92.0 NA 0.04 +204 NA 160 ~ 

370(+) 

NA 0.178 ~ 

0.367 

1.176 231.42 0.0051 

11.5 NA 0.40 +20 NA 8 ~ 

130(+) 

NA 0.046 ~ 

0.152 

14.94 292.45 0.0511 

21.0 NA 0.38 +24 0 300 0 0.304 33.41 292.45 0.1142 

Main Element 

(1997) 

4.0 

92.0 NA 0.30 +85 NA 10 ~ 

420(+) 

NA 0.047 ~ 

0.411 

42.47 292.45 0.1452 

11.5 30 0.29 +14 -4 286++ 0.872 1.092 11.81 231.42 0.0510 21.0 30 0.51 +24 -4 286++ 0.872 1.092 47.96 231.42 0.2072 0 

92.0 30 0.74 +24 -4 286++ 0.872 1.092 96.72 231.42 0.4179 

11.5 30 0.23 +15 -4 286++ 0.872 1.092 9.424 292.45 0.0322 21.0 30 0.53 +16 -4 286++ 0.872 1.092 51.37 292.45 0.1757 

Trailing Edge 

Flap 

(1997) 4.0 

92.0 30 0.78 +22 -4 286++ 0.872 1.092 110.9 292.45 0.3793 

Nomenclature for Table 17 1. The frontal area, f A of the three-element high lift system is defined as follows:

(frontal area for 0 degree of angle of attack) (frontal area for 4 degrees of angle of attack)

2. ‡ end of blotter strip, 3. Certain regions of leading edge slat are located in negative x-axis. 4. (+) traced impingement starts and ends at lower surface 

A

A

NASA/TM—2002-211700 78
108 

Fig. 1a Langmuir “D” dimensionless distribution of droplet sizes. 

0.0 0.5 1.0 1.5 2.0 2.5 3.0

Ratio of Dro

plet Diameter to Median Volumetric Dro

plet Diameter

1.00.90.80.70.60.50.40.30.20.10.0

Cummulative Fraction of Total Liquid Water Content i di/MVD 

∆wi/wt % 

1 0.31 52 0.52 103 0.71 204 1.00 305 1.37 206 1.74 107 2.22 5 ,

∆w1/wt 

∆w2/wt 

∆w3/wt 

∆w4/wt 

∆w5/wt 

∆w6/wt 

∆w7/wt 

ContinuousDiscrete

NASA/TM—2002-211700 79
Fig. 1b Definition of local impingement efficiency for a body

in a cloud of uniform droplet size.

Fig. 1c Two-dimensional droplet trajectories for a body

in a cloud of uniform droplet size.

• V• n //

dAs = nsdAs

dA• = n•dA•

LWC V dA LWCsVs dAs ◊ = ◊ • • •

LWC V dA LWCs ( ns Vs )dAs ◊ = - ◊ • • •

( )

• •

• - ◊ = = LWC V

LWC n V

dA

dA s s s

s

b

NASA/TM—2002-211700 80
Fig. 2 Plan view of NASA Glenn Icing Research Tunnel (IRT).

Fig. 3 Icing Research Tunnel turntable and model mounting plate

(all dimensions are given in inches).

NASA/TM—2002-211700 81
Fig. 4 IRT test section north and south walls showing visual access windows,

turntable, and altitude exhaust piping.

Fig. 5 Schematic of an IRT spray nozzle.

Water tube diameter of an IRT nozzle:

Standard Nozzle – 0.025 inches

Mod-1 Nozzle – 0.015 inches

NASA/TM—2002-211700 82
Fig. 6 IRT icing cloud operating envelopes for standard nozzles.

Fig. 7 IRT icing cloud operating envelopes for MOD-1 type nozzles.

NASA/TM—2002-211700 83
Fig. 8a MS(1)-0317 medium speed airfoil section.

Fig. 8b MS(1)-0317 airfoil installation in IRT test section (top view).

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.5

-0.4

-0.3

-0.2

-0.1

0.0

0.1

0.2

0.3

0.4

0.5

Y/ C

MS(1)-0317

Turntable Center

(x/c = 0.42, y/c = 0, c = 36 in.)

Secondary Control Room Tunnel Wall

104” Dia.

Turntable

Tunnel Wall Primary Control Room

Air Flow

y

53.82”

54.0”

x

+ A.O.A.

 + Turntable

North Wall

South Wall

15.12”

20.88”

Lower Surface

Upper Surface

 +a

 +a

Rotation Pivot

NASA/TM—2002-211700 84
looking downstream looking upstream

Fig. 8c MS(1)-0317 airfoil installed in IRT test section.

NASA/TM—2002-211700 85
Fig. 9a GLC-305 airfoil section.

Fig. 9b GLC-305 airfoil installation in IRT test section (top view).

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.5

-0.4

-0.3

-0.2

-0.1

0.0

0.1

0.2

0.3

0.4

0.5

Y/ C

GLC 305

Turntable Center

(x/c = 0.28, y/c = 0.01, c = 35.5 in.)

104” Dia.

Turntable

Air Flow

53.82”

54.0”

+ A.O.A.

 + Turntable

Secondary Control Room Tunnel Wall

Tunnel Wall Primary Control Room

y

x

North Wall

South Wall

25 92”

Lower Surface

Rotation Pivot

Upper Surface

 +a

 +a

NASA/TM—2002-211700 86

10 08”
Fig. 9c GLC-305 airfoil installed in IRT test section (looking downstream).

NASA/TM—2002-211700 87
Fig. 10a NACA 652-415 airfoil section.

Fig. 10b NACA 652-415 airfoil installation in IRT test section (top view).

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.5

-0.4

-0.3

-0.2

-0.1

0.0

0.1

0.2

0.3

0.4

0.5

Y/ C

NACA 652-415 

Turntable Center

(x/c = 0.5, y/c = 0, c = 36 in.)

104” Dia.

Turntable

Air Flow

53.82”

54.0”

 + A.O.A.

 + Turntable

Secondary Control Room Tunnel Wall

Tunnel Wall Primary Control Room

y

x

North Wall

South Wall

18”

18”

Upper Surface

Rotation Pivot

Lower Surface

 +a

 +a

NASA/TM—2002-211700 88
Fig. 10c NACA 652-415 airfoil installed IRT test section (looking downstream).

NASA/TM—2002-211700 89
Fig. 11a Commercial transport horizontal tail section.

Fig. 11b Commercial transport horizontal tail installation in IRT test section (top view).

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.5

-0.4

-0.3

-0.2

-0.1

0.0

0.1

0.2

0.3

0.4

0.5

Y/ C

Boeing 757 Tail

Turntable Center

(x/c = 0.33, y/c = 0, c = 35.44 in.)

Commercial Transport Tail Section

104” Dia.

Turntable

Air Flow

53.82”

54.0”

+ A.O.A.

+ Turntable

Secondary Control Room Tunnel Wall

Tunnel Wall Primary Control Room

y

x

North Wall

South Wall

25.92”

10.08”

Pressure Surface

Rotation Pivot

Suction Surface

Suction Surface

Pressure Surface

+a

 +a

NASA/TM—2002-211700 90
Fig. 11c Commercial transport horizontal tail installed in IRT test section

 (looking downstream).

NASA/TM—2002-211700 91
Fig. 12a NLF(1)-0414 36-in airfoil section.

Fig. 12b NLF(1)-0414 36-in airfoil installation in IRT test section (top view).

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.5

-0.4

-0.3

-0.2

-0.1

0.0

0.1

0.2

0.3

0.4

0.5

Y/ C

NLF(1)-0414

Turntable Center

(x/c = 0.323, y/c = 0, c = 36 in.)

104” Dia.

Turntable

Air Flow

53.82”

54.0”

+ A.O.A.

+ Turntable

Secondary Control Room Tunnel Wall

Tunnel Wall Primary Control Room

y

x

North Wall

South Wall

Lower Surface

24.37”

11.63”

Upper Surface

Rotation Pivot

 +a

 +a

NASA/TM—2002-211700 92
Fig. 12c NLF(1)-0414 36-in airfoil installed in IRT test section (looking downstream).

NASA/TM—2002-211700 93
Fig. 13a NLF(1)-0414 48-in airfoil section.

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.5

-0.4

-0.3

-0.2

-0.1

0

0.1

0.2

0.3

0.4

0.5

Y/ C

NLF(1)-0414F

Turntable Center

(x/c=0.5, y/c=0, c=48 in)

24”

Upper Surface

24”

Rotation Pivot

Lower Surface

104” Dia.

Turntable

Air Flow

53.82”

54.0”

+ A.O.A.

+ Turntable

Secondary Control Room Tunnel Wall

Tunnel Wall Primary Control Room

y

x

North Wall

South Wall

 +a

 +a

Fig. 13b NLF(1)-0414 48-in airfoil installation in IRT test section (top view).

NASA/TM—2002-211700 94
looking downstream looking upstream

Fig. 13c NLF(1)-0414 48-in airfoil installed in IRT test section.

NASA/TM—2002-211700 95
Fig. 14a NACA 64A008 swept tail.

Fig. 14b NACA 64A008 swept tail installation in IRT test section (top view).

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.5

-0.4

-0.3

-0.2

-0.1

0.0

0.1

0.2

0.3

0.4

0.5

Y/ C

NACA 64A008

Turntable Center

(x/c = 0.208, y/c = 0, c = 45.75 in.)

x

y

Secondary Control Room Tunnel Wall

104” Dia.

Turntable

Tunnel Wall Primary Control Room

Air Flow

53.82”

54.0”

+ A.O.A.

+ Turntable

North Wall

South Wall

Lower Surface

Rotation Pivot 36.23”

Upper Surface

9.52”

 +a

 +a

NASA/TM—2002-211700 96
NACA 64A008 Airfoil

 Taper Ration = 0.62

 Wing Area = 1767.6 in2

 Aspect Ration = 2.6

 Leading Edge Sweep Angle = 29.1∞

 Trailing Edge Sweep Angle = 11.1∞

 (Side View) (Front View)

 (Bottom View)

Fig. 14c NACA 64A008 swept tail (3-View Plot).

Cylindrical End Cap

NACA 64A008

119.1∞ 101.1∞

 45.75”

 26.714” 28.163”

48”

24”

43”

Pressure Taps

(30 Each Station)

NASA/TM—2002-211700 97
Fig. 14d NACA 64A008 swept tail installed in IRT test section (looking downstream).

looking downstream

Inboard Strip LocationStrip A: 36 inch fromtunnel floor

NASA/TM—2002-211700 98
Fig. 15a 25%-scale business jet empennage horizontal tail section.

Fig. 15b 25%-scale business jet empennage installation in IRT test section (top view).

Rotation

Pivot

7.04”

29.1∞

Flow

Direction

1.75”

104” Dia.

53.82”

54.0”

25.79”

58.75”

Secondary Control Room 

Primary Control Room

Turntable

Tunnel Wall

Tunnel Wall

South Wall

North Wall

16.35”

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.5

-0.4

-0.3

-0.2

-0.1

0

0.1

0.2

0.3

0.4

0.5

Y/ C

Business Jet Tail Section

suction surface

pressure surface

Lift (-ve)

+ Pitching Moment

-a

NASA/TM—2002-211700 99
Fig. 15c Business jet empennage and mounting device (side view).

Fig. 15d Business jet empennage mounting device.

back view of mounting device

+a

-a

+a

0 deg.

-a

Flow

pressure surface

suction surface

NASA/TM—2002-211700 100
Fig. 15e 25%-scale business jet empennage installed in IRT test section.

Looking upstream

Looking downstream

Inboard Strip Location

Strip A: 19.2 inch from tail tip

Outboard Strip Location

Strip B: 11.5 inch from tail tip

NASA/TM—2002-211700 101
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.5

-0.4

-0.3

-0.2

-0.1

0

0.1

0.2

0.3

0.4

0.5

Y/ C

Business Jet Tail Section

suction surface

pressure surface

Lift (-ve)

+ Pitching Moment

+a

Fig. 16a Full-scale business jet horizontal tail section.

Fig. 16b Full-scale business jet horizontal tail installation in IRT test section (top view).

23.75”

48.82”

28.16”

Rotation Pivot

Root

Tip

104” Dia.

Turntable

Air Flow

53.82”

54.0”

+ A.O.A.

+ Turntable

Secondary Control Room Tunnel Wall

Tunnel Wall Primary Control Room

y

x

North Wall

South Wall

 +a

NASA/TM—2002-211700 102
Looking downstream

Close-up of tip section

Inboard Strip Location

Strip A:28.5 inch from tail tip

Outboard Strip Location

Strip B:21 inch from tail tip

Fig. 16c Full-scale business jet horizontal tail installed in IRT test section.

NASA/TM—2002-211700 103
Fig. 17a Three-element high lift system.

Fig. 17b Three-element high lift system installation in IRT test section (top view).

-0.2 -0.1 0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2

X/C

-0.7

-0.6

-0.5

-0.4

-0.3

-0.2

-0.1

0.0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

Y/ C

Turntable Center

(x/c = 0.39, y/c = 0, based on

deflected chord of 43.875 in.)

WRP

Three-element High Lift System

104” Dia.

Turntable

Air Flow

53.82”

54.0”

+ A.O.A.

+ Turntable

Secondary Control Room Tunnel Wall

Tunnel Wall Primary Control Room

y

x

North Wall

South Wall

17.111”

26.764”

Lower Surface

Rotation Pivot

Upper Surface

 +a

 +a

NASA/TM—2002-211700 104
Fig. 17c Three-element high lift system installed in IRT test section (looking downstream).

looking upstream looking downstream

NASA/TM—2002-211700 105
Fig. 18 Comparison of airfoil sections for 2-D models.

Fig. 19 Close up of leading edge geometry 2-D models.

-0.02 0 0.02 0.04 0.06 0.08 0.1 0.12 0.14 0.16 0.18 0.2

X/C

-0.12

-0.11

-0.1

-0.09

-0.08

-0.07

-0.06

-0.05

-0.04

-0.03

-0.02

-0.01

0

0.01

0.02

0.03

0.04

0.05

0.06

0.07

0.08

0.09

0.1

Y/ C

MS(1)-0317

GLC 305

Commerical Transport Tail Section

NLF(1)-0414

NACA 652-415

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.5

-0.4

-0.3

-0.2

-0.1

0

0.1

0.2

0.3

0.4

0.5

Y/ C

MS(1)-0317

GLC 305

Commerical Transport Tail Section

NLF(1)-0414

NACA 652-415

NASA/TM—2002-211700 106
Fig. 20 Comparison of airfoil sections for 3-D models.

Fig. 21 Close up of leading edge geometry 3-D models.

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.5

-0.4

-0.3

-0.2

-0.1

0

0.1

0.2

0.3

0.4

0.5

Y/ C

NACA 64A008

Business Jet Tail Section

-0.02 0 0.02 0.04 0.06 0.08 0.1 0.12 0.14 0.16 0.18 0.2

X/C

-0.12

-0.11

-0.1

-0.09

-0.08

-0.07

-0.06

-0.05

-0.04

-0.03

-0.02

-0.01

0

0.01

0.02

0.03

0.04

0.05

0.06

0.07

0.08

0.09

0.1

Y/ C

NACA 64A008

Business Jet Tail Section

NASA/TM—2002-211700 107
Fig. 22a S-duct engine inlet configuration.

Inlet Length

Offset

Inlet Lip Highlight (ILH)

Splitter nose

Scavenge duct

Throat Engine Inlet

Torque Housing

Engine duct

NASA/TM—2002-211700 108
 

Fig. 22b S-duct engine inlet section views (front and side). 

Fig. 22c S-duct engine inlet. 

Splitter nose 

Engine duct 

Scavenge duct 

Highlight

NASA/TM—2002-211700 109
Fig. 22d S-duct engine inlet geometry definition (side view). 

 

 

Fig. 22e S-duct engine inlet axial cuts (front view, looking downstream). 

Axial Cut, X = 0 Axial Cut, X = 10 Axial Cut, X = 20 

Axial Cut, X = 30 Axial Cut, X = 40 Axial Cut, X = 50 

NASA/TM—2002-211700 110
Fig. 22f Dimension of S-duct engine inlet (in inches).

39.2”

38.74”

15.73”

16.264”

14.72”

NASA/TM—2002-211700 111
Fig. 22g S-duct engine inlet installed in IRT test section (looking downstream).

looking downstream looking upstream

NASA/TM—2002-211700 112
Fig. 22h Blotter strip locations for S-duct engine inlet geometry (looking downstream,

1999 IRT tests.

D strip locates at lower

surface (q = 180∞, see

picture below) of the torque

tube. Highlight for this strip

is located behind the ramp

on the torque tube

A strip is located

at lower lip of

the inlet (see

picture below).

Highlight for this

strip is at ILH

B strip is located at inlet wall

(see picture below). Highlight

for B strip is 13.44” from the

ILH

C strip is located at inlet

“splitter” (see picture below).

Highlight of the C strip is at the

apex of the splitter.

A strip B strip

C strip

C strip

D strip

ILH = Inlet Lip Highlight, most forward point on the Inlet Lip (see Figure 22a)

Highlight

of D strip

NASA/TM—2002-211700 113
Fig. 23 Schematic of Original WSU 12–nozzle spray system used during the 1985 and 1989 impingement tests.

NASA/TM—2002-211700 114
Fig. 24 WSU spray system installed in IRT plenum chamber (1997 IRT entry).

CCD

Camera

Fairing

NASA/TM—2002-211700 115
(1997 WSU spray system; all dimensions in inches) 

WSU Nozzle 

Assembly # 

NASA MOD-1 

Nozzle # 

Cf Y-Coordinate (in) 

(Notes:1,2) 

Z-Coordinates (in) 

(Note:1) 

1 277 0.00400 -17.250 +6.750/SP5 

2 306 0.00399 -29.375 +6.750/SP4 

3 279 0.00399 -6.750 +11.250/SP3 

4 217 0.00398 +18.500 +8.750/SP3 

5 308 0.00401 +37.000 +17.125/SP4 

6 311 0.00406 +56.500 +11.000/SP5 

7 210 0.00402 +46.250 -4.000/SP7 

8 233 0.00400 +19.750 -4.250/SP7 

9 242 0.00401 -9.500 -6.500/SP7 

10 243 0.00401 -30.250 -4.750/SP7 

11 249 0.00401 +23.750 +10.750/SP5 

12 252 0.00403 -52.000 +9.500/SP5 

1. Positive Y to the right looking upstream measured from trailing edge of center 

beam. 

2. Example: WSU Nozzle Assembly # 11. Y = 23.750 inches to the right of center 

beam, looking upstream. Z = +10.750/SP5, i.e., 10.75 inches above trailing edge 

(upstream edge) of spray bar #5 (SP5). 

Fig. 25 WSU spray system nozzle locations with respect to the IRT spray bars 

 (1997 IRT Entry). 

24 in

48 in

24 in

24 in

24 in

24 in

24 in

24 in

24 in

24 in

175.02 in 175.02 in

Spray Bar #1

Center Support

Wall Beam Wall

Spray Bar #2

Spray Bar #3

Spray Bar #4

Spray Bar #5

Spray Bar #6

Spray Bar #7

Spray Bar #8

Spray Bar #9

Spray Bar #10

IRT Plenum Chamber Floor

IRT Plenum Chamber Ceiling

1

2

3 4

5

6

8 7 10 9

11 12

Z (in) 

Y (in) 

NASA/TM—2002-211700 116
Fig. 26 WSU spray system installed in IRT plenum chamber (1999 IRT entry).

CCD

Camera

Fairing

NASA/TM—2002-211700 117
(1999 WSU spray system; all dimensions in inches) 

WSU Nozzle 

Assembly # 

NASA MOD-1 

Nozzle # 

Cf Y-Coordinate (in) 

(Notes:1,2) 

Z-Coordinates (in) 

(Note:1) 

1 277 0.00400 -17.375 -17.375/SP6 

2 306 0.00399 -31.750 +8.250/SP4 

3 234 0.00399 -6.750 +11.250/SP3 

4 217 0.00398 +7.750 +7.500/SP4 

5 308 0.00401 +37.000 -17.375/SP5 

6 243 0.00406 +56.500 +11.125/SP5 

7 210 0.00402 +46.125 +20.250/SP6 

8 233 0.00400 +9.000 +18.000/SP6 

9 242 0.00401 -9.250 +17.500/SP6 

10 311 0.00401 -37.500 +17.125/SP6 

11 249 0.00401 +24.000 +11.000/SP5 

12 252 0.00403 +26.000 +17.000/SP6 

Fig. 27 WSU spray system nozzle locations with respect to the IRT spray bars 

(1999 IRT entry). 

12 

•

24 in

48 in

24 in

24 in

24 in

24 in

24 in

24 in

24 in

24 in

175.02 in 175.02 in

Spray Bar #1

Center Support

Wall Beam Wall

Spray Bar #2

Spray Bar #3

Spray Bar #4

Spray Bar #5

Spray Bar #6

Spray Bar #7

Spray Bar #8

Spray Bar #9

Spray Bar #10

IRT Plenum Chamber Floor

IRT Plenum Chamber Ceiling

1

2

3 4

5

6

8 7 10 9

11 12

Z (in) 

Y (in) 

•

4 

•

5 

NASA/TM—2002-211700 118
 

Fig. 28 Close up of WSU nozzle assembly. Fig. 29 Stainless steel pressure tank. 

 

Fig. 30 Main air supply control system for WSU spray nozzles. 

Pressure 

Transducer 

Solenoid 

Valve 

Air Line 

MOD-1 

Nozzle 

IRT High Pressure 

Air Supply

Air Filter

Solenoid 

Valve

Shut-off 

Valve

Electropneumatic 

Transducer

Electro-pneumatic 

Transducer

Air Pressure 

Regulator

IRT High Pressure 

Air Supply

NASA/TM—2002-211700 119
Fig. 31a Main water supply control system for WSU spray nozzles.

Fig. 31b Schematic of Improved WSU 12–nozzle spray system used during the 1997

and 1999 impingement tests.

Ball Valve

Electro-pneumatic

Transducer

Air Pressure

Regulator

NASA/TM—2002-211700 120
Fig. 32 Simplified data acquisition system block diagram. 

Fig. 33 6-ft by 6-ft uniformity grid with/without blotter squares or strips. 

PERSONAL COMPUTER

ANALOG-TODIGITAL 

CIRCUIT CARD 

DIGITAL 

INPUT/OUTPUT 

CIRCUIT CARD

TRANSDUCER 

EXCITATION 

(VDC PWR SUPPLY)

+Exc -Exc

Transducer # 1

Transducer # 18

SOLID 

STATE 

RELAYS 

(13) 

Solenoid # 1 

Solenoid # 13

NASA/TM—2002-211700 121
Fig. 34 Argon-Ion laser emission.

Fig. 35 Laser sheet set up.

NASA/TM—2002-211700 122
a. Fiber Optic Collimator

b. Galvanometer

c. Cylindrical Lenses

d. 1999 Argon-Ion laser

beam system

Fig. 36 Key components of Argon-Ion laser beam system (1999 IRT entry).

a b c

d

NASA/TM—2002-211700 123
Fig. 37 Laser sheets axial locations in IRT test section. 

 

Fig. 38 CCD cloud images in IRT test section. 

high LWC area 

uniformity grid 

55.5" 

33.875" 

North Wall Tunnel Wall 

Turntable 

Tunnel Wall 

South Wall 38.75" 

42.5"

Plenum Test Section 

Chamber

4-ft Laser 

Sheet 

Flow 

Direction 

2-ft Laser 

Sheet 

NASA/TM—2002-211700 124
a. Forward Scattering Spectrometer Probe (FSSP) optical configuration.

b. FSSP installed in IRT test section

Fig. 39 Forward Scattering Spectrometer Probe (FSSP).

looking downstream

Sample

Volume

5 mW

He-Ne Laser

Photodiode

(Annulus)

Photodiode

(Signal)

Dump

Spot

67% Beam

Splitter FL. 8 55 mm

Lens Pack

Air

Flow

Dump Spot

Right Angle

Prism

45 deg. Mirror

Condensing

Lens (60 mm)

NASA/TM—2002-211700 125
Fig. 40 Optical Array Probe (OAP). 

 

Fig. 41 King Probe installed in IRT test section. 

close-up of King Probe looking downstream 

Air 

Flow

1.5 mW 

He-Ne Laser 

24 Element Linear 

Photodiode Array

Secondary 

Zoom Lens

45 deg. Mirror

45 deg. Mirror Objective 

45 deg. Mirror Lens (F60)

NASA/TM—2002-211700 126
Fig. 42a Measured MVD and LWC distributions for 1997 and 1999 IRT tests

(MVD = 11, 11.5 mm) (Continued).

1.00 10.00 100.00

Droplet Diameter (microns)

1.00E-006

1.00E-005

1.00E-004

1.00E-003

1.00E-002 LWC (g/ m3 / micron)

1997 - FSSP

1997 - FSSP - Repeat 1 

1997 - FSSP - Repeat 2 

1999 - FSSP 

1999 - FSSP - Repeat 1

1999 - FSSP - Repeat 2

1.00 10.00 100.00

Droplet Diameter (microns)

1.00E-004

1.00E-003

1.00E-002

1.00E-001

1.00E+000

1.00E+001

1.00E+002

Nu

mber D

e

n

sity (#/c 3

m/ micron)

1997 - FFSP

1997 - FSSP - Repeat 1

1997 - FSSP - Repeat 2 

1999 - FFSP

1999 - FSSP - Repeat 1

1999- FSSP - Repeat 2

NASA/TM—2002-211700 127
Fig. 42b Measured MVD and LWC distributions for 1997 and 1999 IRT tests

(MVD = 21 mm) (Continued).

1.00 10.00 100.00 1000.00

Droplet Diameter (microns)

1.00E-007

1.00E-006

1.00E-005

1.00E-004

1.00E-003

1.00E-002 LWC (g/ m3 / micron)

1997 - FSSP

1997 - OAP

1997 - FSSP - Repeat 1

1997 - FSSP - Repeat 2

1999 - FSSP

1999 - OAP

1999 - FSSP - Repeat 1

1999 - OAP - Repeat 1

1999 - FSSP - Repeat 2

1999 - OAP - Repeat 2

1.00 10.00 100.00 1000.00

Droplet Diameter (microns)

1.00E-007

1.00E-006

1.00E-005

1.00E-004

1.00E-003

1.00E-002

1.00E-001

1.00E+000

1.00E+001

1.00E+002

Nu mber Density #/cm ( 3 / micron)

1997 - FSSP

1997 - OAP

1997 - FSSP - Repeat 1

1997 - FSSP - Repeat 2

1999 - FSSP

1999 - OAP

1999 - FSSP - Repeat 1

1999 - OAP - Repeat 1

1999 - FSSP - Repeat 2

1999 - OAP - Repeat 2

NASA/TM—2002-211700 128
Fig. 42c Measured MVD and LWC distributions for 1997 and 1999 IRT tests

(MVD = 92, 94 mm).

1.00 10.00 100.00 1000.00

Droplet Diameter (microns)

1.00E-006

1.00E-005

1.00E-004

1.00E-003

1.00E-002 LWC (g/ m3 / micr on)

1997 - FSSP

1997 - OAP

1999 - FSSP 

1999 - OAP

1999 - FSSP - Repeat

1999 - OAP - Repeat

1.00 10.00 100.00 1000.00

Droplet Diameter (microns)

1.00E-006

1.00E-005

1.00E-004

1.00E-003

1.00E-002

1.00E-001

1.00E+000

1.00E+001

Nu mber Density (#/cm3 / micr on)

1997 - FSSP

1997 - OAP

1999 - FSSP

1999 - OAP

1999 - FSSP - Repeat

1999 - OAP - Repeat

NASA/TM—2002-211700 129
1”

Fig. 43 Collector mechanism installed in IRT test section.

Fig. 44 Collector blade geometry (not to scale).

NASA/TM—2002-211700 130
Fig. 45 Location of the collector mechanism with respect to the uniformity grid.

Fig. 46 Close up of the reference collector matching the blotter strips locations on a

MS(1)-0317 airfoil.

6" (12)

6" (12)

IRT Test Section Floor

IRT Test Section Ceiling

Strip B location

Strip A location

6-ft by 6-ft

Uniformity

Grid

2-ft high

by 3-ft

wide

uniformity

region

Reference

collector

blades

NASA/TM—2002-211700 131
Fig. 47 Laser Reflectometer calibration curve (Verigood 100# paper, 1997 IRT tests).

0.0 0.5 1.0 1.5 2.0 2.5 3.0 3.5 4.0 4.5

Dye Mass (

μg / cm 2)

1.00.90.80.70.60.50.40.30.20.10.0

Normalized Reflectance

Calibration Equation for Laser Reflectometer(1997 IRT tests)

y =

a+cx+ex 2+gx 3+ix 4+kx 5

1+bx+dx 2+fx 3+hx 4+jx 5

a = 0.9999923 b = 306.1623 c = 309.83718d = 3832.2711 e = 3205.367 f = 4554.6459g = 864.44669 h = -384.597 i = -39.38789 j = 76.32239 k = 15.822399 

NASA/TM—2002-211700 132
0.0 0.5 1.0 1.5 2.0 2.5 3.0 3.5 4.0 4.5

Fig. 48 Laser Reflectometer calibration curve (Verigood 100# blotter paper, 1999 IRT tests).

Dye Mass (

μg / cm2)

1.00.90.80.70.60.50.40.30.20.10.0

Normalized Reflectance

Calibration Equation for Laser Reflectometer(1999 IRT tests)

y = a +

b

1+(x/c)

d

a = -0.0796341 b = 1.0796341 c = 2.3792054d = 0.63310639

NASA/TM—2002-211700 133
0.0 0.5 1.0 1.5 2.0 2.5 3.0 3.5 4.0 4.5

Fig. 49 CCD Reflectometer calibration curve (Verigood 100# blotter paper, 1997 IRT tests).

Dye Mass (

μg / cm 2)

1.00.90.80.70.60.50.40.30.20.10.0

Normalized Reflectance

Calibration Equation for CCD Reflectometer(1997 IRT tests)

y = a + be(-x/c)

a = 0.48281288 b = 0.51323622 c = 0.65490526

NASA/TM—2002-211700 134
0.0 0.5 1.0 1.5 2.0 2.5 3.0 3.5 4.0 4.5

Fig. 50 CCD Reflectometer calibration curve (Verigood 100# blotter paper, 1999 IRT tests). 

Dye Mass (

μg / cm2)

1.00.90.80.70.60.50.40.30.20.10.0

Normalized Reflectance

Calibration Equation for CCD Reflectometer(1999 IRT tests)

y = a + b 

* exp(-cx) + d 

* exp(-ex)

a = 0.2294109 b = 0.1536828 c = 7.863542d = 0.6089803 e = 0.4005039 

NASA/TM—2002-211700 135
a. Schematic of automated laser reflectometer and digital data acquisition system. 

b. Typical raw surface reflectance distribution for a dyed blotter strip 

Fig. 51 Automated Laser Reflectometer data reduction system. 

DRUM

LASER PATH

POWER

SUPPLY

HE-NE LASER

ELECTRIC PATH

POWER

SUPPLY

FILTER

POWER

SUPPLY

LINEAR

ACTUATOR

POWER

SUPPLY

STEPPER

MOTOR

PHOTODETECTOR

CONVERGENT

LENS

SIGNAL

CONDITIONING

UNIT

COMPUTER

(WITH INTERFACE

CIRCUIT CARDS)

PRINTER

DIGITAL

VOLTMETER

DIGITAL

VOLTMETER

PHOTODETECTOR

I/O LINE

TRIGGER

LINE

BLOTTER

STRIP

 GLASS SPLITTER PLATE

-300 -200 -100 0 100 200 300

Surface Distance (m m)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Raw Reflectance

NASA/TM—2002-211700 136
a. Scan locations for test model and reference collector strips 

(laser reflectometer) 

b. Blotter strip image analysis region for CCD data reduction system 

 

c. Scan locations for 3D models (laser 

reflectometer) 

d. V-strip image analysis region for CCD 

data reduction system 

Fig. 52 Blotter strip analysis with laser reflectometer and CCD data reduction 

systems. 

Blotter strip for 

reference collector 0.2” 

2” 

scan 

lines

scan 

highlight lines

mark 

highlight 

mark 

BLOTTER IMAGE ANALYSIS REGION 1.5” 

D

A

B

• 

• 

E •

• F

C 

• 

G •

• 

HORIZONTAL SCAN LINE

20

horizontal scan lines 1.5” 

• User specifies the locations of A, B, C, 

and D 

• Program determines the locations of 

E, F, G, and corresponding region 

BLOTTER 

IMAGE 

ANALYSIS 

REGION 

• V-shape blotter strips for 3D models 

• Sectional scan required 

NASA/TM—2002-211700 137
a. Schematic diagram of the CCD Reflectometer 

b. Typical raw intensity (reflectance) distribution for a dyed blotter strip 

Fig. 53 CCD Reflectometer data reduction system. 

(A) Computer 

(B) CCD Control Unit 

(C) CCD Camera 

(D) Light Units 

(E) Power Supplies for Lights 

(F) Table 

(G) Portable Dark Room 

A

D 

E

F

B

G

C

-300 -200 -100 0 100 200 300

Surface Distance (mm)

4000

5000

6000

7000

8000

9000

10000

11000

12000

13000

14000

Raw I

ntensity

NASA/TM—2002-211700 138
a. NACA 64A008 swept horizontal tail section installation in IRT test section 

b. PMARC panel model for NACA 64A008 swept finite tail 

Fig. 54 NACA 64A008 swept horizontal tail wind tunnel and analytical flow models 

(Continued). 

NASA/TM—2002-211700 139
c. Grid at Y = 0 plane 

d. PMARC panel model and grid 

Fig. 54 NACA 64A008 swept horizontal tail wind tunnel model and analytical flow

NASA/TM—2002-211700 140
a. Full-scale business jet horizontal tail installation in IRT test section 

b. PMARC panel model 

Fig. 55 Wind tunnel and analytical flow model for full-scale business jet horizontal tail 

(Continued). 

NASA/TM—2002-211700 141
c. Grid at Y = 0 plane 

d. PMARC panel model and grid 

Fig. 55 Wind tunnel and analytical flow model for full-scale business jet horizontal tail. 

NASA/TM—2002-211700 142
a. 25%-scale business jet empennage installation in IRT test section 

b. PMARC panel model 

Fig. 56 Wind tunnel and analytical flow model for 25%-scale business Empennage 

(Continued). 

left tail; looking downstream 

NASA/TM—2002-211700 143
c. Grid at Y = 0 plane 

d. PMARC panel model and grid 

Fig. 56 Wind tunnel and analytical flow models for 25%-scale business jet 

empennage. 

NASA/TM—2002-211700 144
 

Fig. 57 Computational grid system (997,450 grid points) for the S-duct engine inlet. 

NASA/TM—2002-211700 145
a. Variation in average tank water pressure.

b. Variation in average air supply pressure. 

Fig. 58 Repeatability of average spray system air and water pressures (1997 tests). 

0 40 80 120 160 200 240 280 320 360 400 440 480

Run Number

0

4

8

12

16

20

24

28

32

36

40

44

48

52

Main Air Pressure (psig)

MVD = 11.5 microns

MVD = 21 microns

MVD = 92 microns

0 40 80 120 160 200 240 280 320 360 400 440 480

Run Number

32

36

40

44

48

52

56

60

64

68

72

76

80

84

Tank Water Pressure (psig)

M VD = 11.5 microns

MVD = 21 microns

MVD = 92 microns

NASA/TM—2002-211700 146
a. Variation in average tank water pressure.

b. Variation in average air supply pressure. 

Fig. 59 Repeatability of average spray system air and water pressures (1999 tests). 

280 320 360 400 440 480 520 560

Run Number

0

5

10

15

20

25

30

35

40

45

50

Main Air Pressure (psig)

M VD = 11 microns

M VD = 21 microns

M VD = 94 microns

280 320 360 400 440 480 520 560

Run Number

30

35

40

45

50

55

60

65

70

75

80

Tank Water Pressure (psig)

MVD = 11 microns

MVD = 21 microns

MVD = 94 microns

NASA/TM—2002-211700 147
a. Variation in βmax with MVD

b. Variation in impingement limits with MVD

Fig. 60 Variation in maximum impingement efficiency and impingement limits with 

MVD for MS(1)-0317 airfoil; computational results obtained with monodispersed 

droplet distribution. 

0 10 20 30 40 50 60 70 80 90 100

Droplet Size (M icrons)

0.0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1.0

Maximum Impingement Efficiency (Beta)

0 deg.

8 deg.

-300 -200 -100 0 100 200 300 400 500

<--- Upper Surface | Low er Surface ---> 

0

10

20

30

40

50

60

70

80

90

100

110

120

130

140

150

160

Droplet Size (Microns)

Surface Distance from H ighlight (m m )

Alpha = 0 deg. 

Alpha = 8 deg. 

NASA/TM—2002-211700 148
 

a. MS(1)-0317 airfoil b. NLF(1)-0414 airfoil 

 

c. 25%-scale business jet empennage d. Full-scale business jet tail section 

Fig. 61 Variation in WSU 12-nozzle spray system water flow rate (1999 tests). 

295 300 305 310 315

Run Number

0.00

0.05

0.10

0.15

0.20

0.25

0.30

0.35

0.40

0.45

0.50

Flow Rate (gpm)

MVD = 11 microns

MVD = 21 microns

MVD = 94 microns

380 385 390 395 400

Run Number

0.00

0.05

0.10

0.15

0.20

0.25

0.30

0.35

0.40

0.45

0.50

Flow Rate (gpm)

MVD = 11 microns

MVD = 21 microns

MVD = 94 microns

485 490 495 500 505 510

Run Number

0.00

0.05

0.10

0.15

0.20

0.25

0.30

0.35

0.40

0.45

0.50

Flow Rate (gpm)

MVD = 11 microns

MVD = 21 microns

MVD = 94 microns

435 440 445 450 455 460

Run Number

0.00

0.05

0.10

0.15

0.20

0.25

0.30

0.35

0.40

0.45

0.50

Flow Rate (gpm)

MVD = 11 microns

MVD = 21 microns

MVD = 94 microns

NASA/TM—2002-211700 149
 

 

 

Fig. 62 Spray system pressures versus spray time for all MVD cases (1997 tests). 

0 5 10 15 20

Time (sec)

35

40

45

50

55

60

65

70

Pressure (psig)

Nozzle 1 (Water Pressure)

Tank (Water Pressure)

Nozzle 1 (Air Pressure)

Main Air Supply Pressure

A1. Run 174 - MVD = 11.5 microns

0.0 0.5 1.0 1.5 2.0

Time (sec)

35

40

45

50

55

60

65

70

Pressure (psig)

Nozzle 1 (Water Pressure)

Tank (Water Pressure)

Nozzle 1 (Air Pressure)

Main Air Supply Pressure

A2. Run 174 - MVD = 11.5 microns (First 2 seconds)

0.0 0.5 1.0 1.5 2.0

Time (sec)

0

10

20

30

40

50

60

70

80

Pressure (psig)

Nozzle 1 (Water Pressure)

Tank (Water Pressure)

Nozzle 1 (Air Pressure)

Main Air Supply Pressure

B2. Run 350 - MVD = 21 microns (First 2 seconds)

0.0 0.5 1.0 1.5 2.0 2.5 3.0

Time (sec)

0

5

10

15

20

25

30

35

40

45

Pressure (psig)

Nozzle 1 (Water Pressure)

Tank (Water Pressure)

Nozzle 1 (Air Pressure)

Main Air Supply Pressure

C1. Run 416 - MVD = 92 microns 

0.0 0.2 0.4 0.6 0.8 1.0

Time (sec)

0

5

10

15

20

25

30

35

40

45

Pressure (psig)

Nozzle 1 (Water Pressure)

Tank (Water Pressure)

Nozzle 1 (Air Pressure)

Main Air Supply Pressure

C2. Run 416 - MVD = 92 microns (First second)

0.0 0.2 0.4 0.6 0.8 1.0

Time (sec)

0

10

20

30

40

50

60

70

80

Pressure (psig)

Nozzle 1 (Water Pressure)

Tank (Water Pressure)

Nozzle 1 (Air Pressure)

M ain Air Supply Pressure

B2. Run 350 - MVD = 21 microns (First seconds)

NASA/TM—2002-211700 150
 

 

 

Fig. 63 Spray system pressures versus spray time for all MVD cases (1999 tests). 

0 1 2 3 4 5 6 7 8 9 10

Time (sec)

30

35

40

45

50

55

60

65

70

Pressure (psig)

Nozzle 1 (W ater Pressure)

Tank (W ater Pressure)

Nozzle 1 (Air Pressure)

Main Air Supply Pressure

A1. Run 301 - M VD = 11 m icrons (spray tim e = 9 sec.)

0 0.5 1 1.5 2

Time (sec)

30

35

40

45

50

55

60

65

70

Pressure (psig)

Nozzle 1 (W ater Pressure)

Tank (Water Pressure)

Nozzle 1 (Air Pressure)

Main Air Supply Pressure

A2. Run 301 - M VD = 11 microns (First 2 seconds)

01234

Time (sec)

0

10

20

30

40

50

60

70

80

Pressure (psig)

Nozzle 1 (W ater Pressure)

Tank (W ater Pressure)

Nozzle 1 (Air Pressure)

Main Air Supply Pressure

B1. Run 456 - M VD = 21 m icrons (Spray Time = 3.8 sec.)

0 0.5 1

Time (sec)

0

10

20

30

40

50

60

70

80

Pressure (psig)

Nozzle 1 (W ater Pressure)

Tank (W ater Pressure)

Nozzle 1 (Air Pressure)

M ain Air Supply Pressure

B2. Run 456 - MVD = 21 microns (First 1 seconds)

0 0.5 1 1.5 2 2.5

Time (sec)

0

5

10

15

20

25

30

35

40

Pressure (psig)

Nozzle 1 (W ater Pressure)

Tank (W ater Pressure)

Nozzle 1 (Air Pressure)

Main Air Supply Pressure

C1. Run 552 - MVD = 94 microns (Spray Time = 2.2 sec.)

0 0.2 0.4 0.6 0.8 1

Time (sec)

0

5

10

15

20

25

30

35

40

Pressure (psig)

Nozzle 1 (W ater Pressure)

Tank (Water Pressure)

Nozzle 1 (Air Pressure)

Main Air Supply Pressure

C2. Run 552 - MVD = 94 microns (First second)

NASA/TM—2002-211700 151
Fig. 64 Cloud uniformity tests using IRT uniformity grid; 

1999 impingement tests, MVD = 11 microns. 

0 6 12 18 24 30 36

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Normalized

Reflectance

24" below the tunnel ceiling

left --> right, looking downstream

0 6 12 18 24 30 36

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Normalized

Reflectance

30" below the tunnel ceiling

left --> right, looking downstream

no data obtained 

for this section

0 6 12 18 24 30 36

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Normalized

Reflectance

36" below the tunnel ceiling 

left --> right, looking downstream

0 6 12 18 24 30 36

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Normalized

Reflectance

42" below the tunnel ceiling

left --> right, looking downstream

0 6 12 18 24 30 36

Horizontal Distance (inch)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Normalized

Reflectance

48" below the tunnel ceiling

left --> right, looking downstream

NASA/TM—2002-211700 152
 

Fig. 65 Cloud uniformity tests using IRT uniformity grid; 

1999 impingement tests, MVD = 21 microns. 

0 6 12 18 24 30 36

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

NormalizedReflectance

24" below the tunnel ceiling

left --> right, looking downstream

0 6 12 18 24 30 36

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Normalized

Reflectance

30" below the tunnel ceiling

left --> right, looking downstream

no data obtained 

for this section

0 6 12 18 24 30 36

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Normalized

Reflectance

36" below the tunnel ceiling

left --> right, looking downstream

no data obtained 

for this section

0 6 12 18 24 30 36

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Normalized

Reflectance

42" below the tunnel ceiling

left --> right, looking downstream

no data obtained 

for this section

0 6 12 18 24 30 36

Horizontal Distance (inch)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Normalized

Reflectance

48" below the tunnel ceiling

left --> right, looking downstream

no data obtained 

for this section

NASA/TM—2002-211700 153
Fig. 66 Cloud uniformity tests using IRT uniformity grid; 

1999 impingement tests, MVD = 94 microns. 

0 6 12 18 24 30 36

Horizontal Distance (inch)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Normalized

Reflectance

48" below the tunnel ceiling

left --> right, looking downstream

no data obtained 

for this section

0 6 12 18 24 30 36

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Normalized

Reflectance

24" below the tunnel ceiling

left --> right, looking downstream

no data obtained

 for this section

0 6 12 18 24 30 36

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Normalized

Reflectance

30" below the tunnel ceiling

left --> right, looking downstream

no data obtained 

for this section

0 6 12 18 24 30 36

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Normalized

Reflectance

36" below the tunnel ceiling

left --> right, looking downstream

0 6 12 18 24 30 36

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Normalized

Reflectance

42" below the tunnel ceiling

left --> right, looking downstream

NASA/TM—2002-211700 154
a. 9-inch hrizontal blade (1997 IRT tests) 

b. 9-inch vertical blade (1999 IRT tests) 

Fig. 67 Test repeatability for reference collector mechanism. 

10 20 30 40 50 60 70 80 90 100 110 120 130

0.0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1.0

Norm alized Reflectance 

Surface Distance (mm)

M VD = 21 M icrons

(Laser Reflectometer)

Average of all Runs( Norm. Refl. = 0.509)

Run #476 (Av. Norm. Refl. = 0.495)

Run #477 (Av. Norm. Refl. = 0.513)

Run #478 (Av. Norm. Refl. = 0.516)

Run #479 (Av. Norm. Refl. = 0.513)

Tunnel Center

 Tunnel Left Side 

(looking downstream)

MVD = 21 Microns 

(Laser Reflectometer)

0 20 40 60 80 100 120 140 160 180 200

Surface Distance (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Normalized Reflectance

MVD = 21 Microns

(Laser Reflectometer)

Average of all runs (Norm. Ref. = 0.488)

Run #520 (Av. Norm. Ref. = 0.483)

Run #521 (Av. Norm. Ref. = 0.493)

Run #522 (Av. Norm. Ref. = 0.496)

Run #523 (Av. Norm. Ref. = 0.484)

Run #524 (Av. Norm. Ref. = 0.495)

Run #525 (Av. Norm. Ref. = 0.478)

Tunnel Center

(looking downstream)

Towards Tunnel Ceiling

Towards Tunnel Floor

NASA/TM—2002-211700 155
a. 1997 IRT tests 

b. 1999 IRT tests 

Fig. 68 Effect of relative humidity on LWC. 

50 60 70 80 90 100

Humidity (%)

0.00

0.05

0.10

0.15

0.20

0.25

0.30

0.35

0.40

LWC in grams per m^3

MVD=11.5 um (KING Probe)

MVD= 21 um (KING Probe)

MVD = 92 um (KING Probe)

MVD=11.5 um (FSSP Probe)

MVD= 21 um (FSSP Probe)

50 55 60 65 70 75 80 85 90

Relative Humidity (%)

0.00

0.05

0.10

0.15

0.20

0.25

0.30

0.35

0.40

LWC (g/m3)

N A SA Glenn K ing Probe

M VD = 11 m icrons

M VD = 21 m icrons

M VD = 94 m icrons

NASA/TM—2002-211700 156
Fig. 69 Normalized reflectance obtained with the laser reflectometer versus dye 

mass for three types of blotter paper. 

Fig. 70 Normalized reflectance obtained with the CCD reflectometer versus dye 

mass for three types of blotter paper. 

0.00 0.50 1.00 1.50 2.00 2.50 3.00

Dye Mass (micrograms/cm^2)

0.30

0.40

0.50

0.60

0.70

0.80

0.90

1.00

Normalized Reflectance

Laser Reflectometer

VG100# 

VG80# 

W3MM 

0.00 0.50 1.00 1.50 2.00 2.50 3.00

Dye Mass (micrograms/cm^2)

0.30

0.40

0.50

0.60

0.70

0.80

0.90

1.00

Normalized Reflectance

CCD Reflectometer

VG100#

VG80#

W3MM

NASA/TM—2002-211700 157
a. Laser Reflectometer 

b. CCD Reflectometer

Fig. 71 Repeatability of data reduction systems (1997 tests). 

0 25 50 75 100 125 150 175 200 225

Blotter Surface Distance (mm)

0.95

1.00

1.05

1.10

Raw Reflectance of a 

White Blotter Strip

Note: One symbol every 25 data points

Scan 1 (Aver.=1.019)

Scan 2 (Aver.=0.999)

Scan 3 (Aver.=0.996)

Scan 4 (Aver.=1.009)

Average of four scans 

0 100 200 300 400 500

Blotter Surface Distance (pixels)

12500

13000

13500

14000

Raw Reflectance of a 

White Blotter Strip

Note: One symbol every 25 data points

Scan 1 (Aver.=13,041)

Scan 2 (Aver.=13,133)

Scan 3 (Aver.=13,115)

Scan 4 (Aver.=13,123)

Average of four scans 

NASA/TM—2002-211700 158
a. Laser Reflectometer 

b. CCD Reflectometer 

Fig. 72 Repeatability of data reduction systems (1999 tests). 

0 20 40 60 80 100 120

Blotter Surface Distance (mm)

0.90

0.95

1.00

1.05

Raw Reflectance of a

White Blotter Strip

N ote: One sym bol every 15 data points

Scan 1 (Average = 0.962)

Scan 2 (Average = 0.955)

Scan 3 (Average = 0.959)

Scan 4 (Average = 0.940)

Average of four scans

0 50 100 150 200 250 300 350 400 450

Blotter Surface Distance (pixels)

12500

13000

13500

14000

14500

Raw Reflectance of a

White Blotter Strip

N ote: One symbol every 20 data points

Scan 1 (Average = 13,498)

Scan 2 (Average = 13,506)

Scan 3 (Average = 13,515)

Scan 4 (Average = 13,529)

Average of four scans

NASA/TM—2002-211700 159
a. α = 0°, M = 0.23, Re = 4.9 million 

b. α = 8°, M = 0.23, Re = 4.9 million 

Fig. 73 Comparison of pressure distributions for MS(1)-0317 airfoil. 

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

-4.0

-3.5

-3.0

-2.5

-2.0

-1.5

-1.0

-0.5

0.0

0.5

1.0

Pressure Coefficient, Cp

X/C

MS 317 Airfoil

Analysis (A.O.A. = 0 deg.)

Analysis (A.O.A. = -1.85 deg.)

Experiment (A.O.A. = 0 deg.)

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

-4.0

-3.5

-3.0

-2.5

-2.0

-1.5

-1.0

-0.5

0.0

0.5

1.0

Pressure Coefficient, Cp

X/C

MS 317 Airfoil

Analysis (A.O.A. = 8.0 deg.)

Analysis (A.O.A. = 6.15 deg.)

Experiment (A.O.A. = 8 deg.)

NASA/TM—2002-211700 160
 a. α = 1.5°, M = 0.23, Re = 4.83 million 

b. α = 6°, M = 0.23, Re = 4.83 million 

Fig. 74 Comparison of pressure distributions for GLC-305 airfoil. 

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

1.0

0.5

0.0

-0.5

-1.0

-1.5

-2.0

-2.5

-3.0

-3.5

-4.0

-4.5

-5.0

Pressure Coefficient, Cp

GLC-305 Airfoil

LEWICE2D (A.O.A. = 5.25 deg.)

Experiment (A.O.A. = 6.0 deg.)

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

1.0

0.5

0.0

-0.5

-1.0

-1.5

-2.0

-2.5

-3.0

-3.5

-4.0

-4.5

-5.0

Pressure Coefficient, Cp

GLC-305 Airfoil

LEWICE2D (A.O.A. = 1.6 deg.)

Experiment (A.O.A. = 1.5 deg.)

NASA/TM—2002-211700 161
a. α = 0°, M = 0.23, Re = 4.85 million 

b. α = 8°, M = 0.23, Re = 4.85 million 

Fig. 75 Comparison of pressure distributions for NACA 652-415 airfoil. 

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

1.0

0.5

0.0

-0.5

-1.0

-1.5

-2.0

-2.5

-3.0

-3.5

-4.0

-4.5

-5.0

Pressure Coefficient, Cp

NACA 652-415 Airfoil

LEWICE2D (A.O.A. = -0.55 deg.)

Experiment (A.O.A. = 0 deg.)

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

1.0

0.5

0.0

-0.5

-1.0

-1.5

-2.0

-2.5

-3.0

-3.5

-4.0

-4.5

-5.0

Pressure Coefficient, Cp

NACA 652 -415 Airfoil

LEWICE2D (A.O.A. = 6.55 deg.)

Experiment (A.O.A. = 8 deg.)

NASA/TM—2002-211700 162
a. α = 0°, M = 0.23, Re = 4.84 million 

b. α = 4°, M = 0.23, Re = 4.84 million 

Fig. 76 Comparison of pressure distributions for commercial transport horizontal tail. 

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

1.0

0.5

0.0

-0.5

-1.0

-1.5

-2.0

Pressure Coefficient, Cp

Commercial Transport Tail Section

LEWICE2D (A.O.A. = 0 deg.)

Experiment (A.O.A. = 0 deg.)

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

1.0

0.5

0.0

-0.5

-1.0

-1.5

-2.0

Pressure Coefficient, Cp

Commercial Transport Tail Section

LEWICE2D (A.O.A. = 4 deg.)

Experiment (A.O.A. = 4 deg.)

NASA/TM—2002-211700 163
a. α = 0°, M = 0.23, Re = 4.84 million 

b. α = 8°, M = 0.23, Re = 4.84 million 

Fig. 77 Comparison of pressure distributions for 36-inch NLF(1)-0414 airfoil. 

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

1.0

0.5

0.0

-0.5

-1.0

-1.5

-2.0

-2.5

-3.0

-3.5

-4.0

-4.5

-5.0

Pressure Coefficient, Cp

36" NLF(1)-0414 Airfoil

LEW ICE2D (A.O.A. = 5.5 deg.)

Experim ent (A.O.A. = 8 deg.)

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

1.0

0.5

0.0

-0.5

-1.0

-1.5

-2.0

-2.5

-3.0

-3.5

-4.0

-4.5

-5.0

Pressure Coefficient, Cp

36" NLF(1)-0414 Airfoil

LEW ICE2D (A.O.A. = -1.0 deg.)

Experim ent (A.O.A. = 0 deg.)

NASA/TM—2002-211700 164
a. α = 0°, M = 0.23, Re = 6.53 million 

b. α = 8°, M = 0.23, Re = 6.53 million 

Fig. 78 Comparison of pressure distributions for 48-inch NLF(1)-0414 airfoil. 

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

1.0

0.5

0.0

-0.5

-1.0

-1.5

-2.0

-2.5

-3.0

-3.5

-4.0

-4.5

-5.0

Pressure Coefficient, Cp

48" NLF(1)-0414 Airfoil

LEWICE2D (A.O.A. = -0.75 deg.)

Experiment (A.O.A. = 0 deg., Main Element)

Experiment (A.O.A. = 0 deg., Flap Element)

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

1.0

0.5

0.0

-0.5

-1.0

-1.5

-2.0

-2.5

-3.0

-3.5

-4.0

-4.5

-5.0

Pressure Coefficient, Cp

48" NLF(1)-0414 Airfoil

LEWICE2D (A.O.A. = 6.0 deg.)

Experiment (A.O.A. = 8.0 deg., Main Element)

Experiment (A.O.A. = 8.0 deg., Flap Element)

NASA/TM—2002-211700 165
a. α = 0°, M = 0.23, Re = 5.03 million 

b. α = 6°, M = 0.23, Re = 5.03 million 

Fig. 79 Comparison of pressure distributions for NACA 64A008 finite swept tail. 

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

1.0

0.5

0.0

-0.5

-1.0

-1.5

-2.0

-2.5

-3.0

Pressure Coefficient, Cp

NACA 64A008 Finite Swept Wing Section

LEWICE3D (A.O.A. = 6.25 deg., Inboard)

LEWICE3D (A.O.A. = 6.25 deg., Outboard)

Experiment (A.O.A. = 6.0 deg., Inboard)

Experiment (A.O.A. = 6.0 deg., Outboard)

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

1.0

0.5

0.0

-0.5

-1.0

-1.5

-2.0

-2.5

-3.0

Pressure Coefficient, Cp

NACA 64A008 Finite Swept Wing Section

LEWICE3D (A.O.A. = 0 deg., Inboard)

LEWICE3D (A.O.A. = 0 deg., Outboard)

Experiment (A.O.A. = 0 deg., Inboard)

Experiment (A.O.A. = 0 deg., Outboard)

NASA/TM—2002-211700 166
a. α = -1°, M = 0.23, Re = 1.49 million 

b. α = -6°, M = 0.23, Re = 1.49 million 

Fig. 80 Comparison of pressure distributions for 25%-scale Business Jet Empennage. 

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

1.0

0.5

0.0

-0.5

-1.0

-1.5

-2.0

-2.5

-3.0

Pressure Coefficient, Cp

25%-scale Business Jet Empennage

LEWICE3D (A.O.A. = -2.0 deg.)

Experiment (A.O.A. = -1.0 deg.)

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

1.0

0.5

0.0

-0.5

-1.0

-1.5

-2.0

-2.5

-3.0

Pressure Coefficient, Cp

25%-scale Business Jet Empennage

LEWICE3D (A.O.A. = -7.0 deg.)

Experiment (A.O.A. = -6.0 deg.)

NASA/TM—2002-211700 167
Fig. 81 Comparison of experimental and INS2D pressure distributions for the three-element high lift system;

α = 0°, M = 0.23, Re = 4.9 million, landing configuration, slat deflection 30 deg., flap deflection 30 deg. 

-0.05 0.00 0.05 0.10 0.15

-6.0-5.0-4.0-3.0-2.0-1.0

0.01.0

Pressure Coefficient, Cp

X/C

Three-Element Airfoil 

SLAT

Analysis (A.O.A. = 0.0 deg.)Experiment (A.O.A. = 0.0 deg.)

0.60 0.70 0.80 0.90 1.00

-6.0-5.0-4.0-3.0-2.0-1.0

0.01.0

X/C

Three-Element Airfoil 

FLAP

Analysis (A.O.A. = 0.0 deg.)Experiment (A.O.A. = 0.0 deg.)

0.00 0.20 0.40 0.60 0.80 1.00

-6.0-5.0-4.0-3.0-2.0-1.0

0.01.0

X/C

Three-Element Airfoil 

MAIN ELEMENT

Analysis (A.O.A. = 0.0 deg.)Experim ent (A.O.A. = 0.0 deg.)

NASA/TM—2002-211700 168
Fig. 82a Comparison of experimental and NPARC pressure distributions for the S-duct 

engine inlet; V∞ = 170 mph, mass flow rate = 23 lbm/sec (Continued).

0 5 10 15 20 25

X (inch)

-1.0

-0.8

-0.6

-0.4

-0.2

0.0

0.2

0.4

0.6

0.8

1.0

Pressure Coefficient, Cp

S-duct Engine Inlet (axial direction, θ = 90 deg.)

NPARC

Experiment

0 5 10 15 20 25 30 35 40 45 50

X (inch)

-2.5

-2.0

-1.5

-1.0

-0.5

0.0

0.5

1.0

1.5

Pressure Coefficient, Cp

S-duct Engine Inlet (axial direction, θ = 0 deg.)

NPARC

Experiment

NASA/TM—2002-211700 169
Fig. 82b Comparison of experimental and NPARC pressure distributions for the S-duct 

engine inlet; V∞ = 170 mph, mass flow rate = 23 lbm/sec (Continued).

0 5 10 15 20 25 30 35

X (inch)

-0.50

-0.25

0.00

0.25

0.50

0.75

1.00

1.25

1.50

Pressure Coefficient, Cp

S-duct Engine Inlet (axial direction, θ = 180 deg.)

NPARC

Experim ent

0 5 10 15 20 25

X (inch)

-0.50

-0.25

0.00

0.25

0.50

0.75

1.00

1.25

1.50

Pressure Coefficient, Cp

S-duct Engine Inlet (axial direction, θ = 270 deg.)

NPARC

Experim ent

NASA/TM—2002-211700 170
Fig. 82c Comparison of experimental and NPARC pressure distributions for the S-duct 

engine inlet; V∞ = 170 mph, mass flow rate = 23 lbm/sec. 

0 90 180 270

Radial Distribution, θ (degree)

-3.00

-2.75

-2.50

-2.25

-2.00

-1.75

-1.50

-1.25

-1.00

-0.75

-0.50

-0.25

0.00

0.25

0.50

0.75

1.00

Pressure Coefficient, Cp

S-duct Engine Inlet (radial distribution at X = 37.24 in.)

NPARC

Experiment

-8 -7 -6 -5 -4 -3 -2 -1 0 1 2 3 4 5 6

X (inch)

-4.0

-3.5

-3.0

-2.5

-2.0

-1.5

-1.0

-0.5

0.0

0.5

1.0

1.5

2.0

2.5

3.0

Pressure Coefficient, Cp

S-duct Engine Inlet (Apex)

NPARC

Experiment

NASA/TM—2002-211700 171
 

 

Fig. 83 Test repeatability for MS-317 airfoil -1997 IRT tests.

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., M VD = 92 μm

Average M aximum β = 0.68

Repeatability = ±9.1%

Average

Run #434

Run #435

Run #436

Run #437

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., MVD = 11.5 μm

Average Maximum β = 0.32

Repeatability = ±12%

Average

Run #418

Run #419

Run #420

Run #421

-90 -60 -30 0 30 60 90 120 150 180

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 8 deg., MVD = 21 μm

Average Maximum β = 0.51

Repeatability = ±7.1%

Average

Run #426

Run #427

Run #428

Run #429

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., MVD = 21 μm

Average Maximum β = 0.52

Repeatability = ±3%

Average

Run #430

Run #431

Run #432

Run #433

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 8 deg., MVD = 92 μm

Average Maximum β = 0.61

Repeatability = ±3.6%

Average

Run #438

Run #439

Run #440

-90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 8 deg., MVD = 11.5 μm

Average Maximum β = 0.25

Repeatability = ±8.8%

Average

Run #422

Run #423

Run #424

Run #425

NASA/TM—2002-211700 172
Fig. 84 Test repeatability for MS-317 airfoil -1999 IRT tests.

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., MVD = 11 μm

Average Maximum β = 0.33

Repeatability = ±5.7%

Average

Run #300

Run #301

Run #302

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., M VD = 94 μm

Average Maximum β = 0.68

Repeatability = ±11%

Average

Run #303

Run #304

Run #305

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., MVD = 21 μm

Average Maximum β = 0.52

Repeatability = ±3.1%

Average

Run #297

Run #298

Run #299

NASA/TM—2002-211700 173
 

 

Fig. 85 Test repeatability for GLC-305 airfoil - 1997 IRT tests.

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 1.5 deg., MVD = 21 μm

Average Maximum β = 0.66

Repeatability = ±8.8%

Average

Run #305

Run #306

Run #307

Run #308

-90 -60 -30 0 30 60 90 120 150 180

 <-- Up per S urface | Lower Su rface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 6 deg., MVD = 21 μm

Average Maximum β = 0.60

Repeatability = ±6.0%

Average

Run #309

Run #310

Run #311

Run #312

-90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 6 deg., MVD = 11.5 μm

Average Maximum β = 0.43

Repeatability = ±16%

Average

Run #314

Run #315

Run #316

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 1.5 deg., MVD = 11.5 μm

Average Maximum β = 0.47

Repeatability = ±8.7%

Average

Run #317

Run #318

Run #320

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Su rface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 1.5 deg., M VD = 92 μm

Average Maximum β = 0.76

Repeatability = ±8.7%

Average

Run #321

Run #322

Run #323

Run #324

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 6 d eg., M VD = 92 μm

A verag e M axim um β = 0.72

R epeatab ility = ±4.9%

Average

Run #325

Run #326

Run #327

Run #328

NASA/TM—2002-211700 174
 

 

 

Fig. 86 Test repeatability for NACA 652-415 airfoil -1997 IRT tests.

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upp er S urface | L ower Su rface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., MVD = 92 μm

Average Maximum β = 0.73

Repeatability = ±7.0%

Average

Run #163

Run #164

Run #165

Run #166

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg ., MVD = 21 μm

A verage Maximum β = 0.62

R ep eatability = ±8.1%

Average

Run #180

Run #181

Run #182

Run #183

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., MVD = 11.5 μm

Average Maximum β = 0.45

Repeatability = ±14%

Average

Run #175

Run #176

Run #178

Run #179

Run #213

Run #214

Run #215

-90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 8 deg., MVD = 11.5 μm

Average Maximum β = 0.30

Repeatability = ±13%

Average

Run #171

Run #172

Run #173

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 8 deg., MVD = 92 μm

Average M axim um β = 0.69

Repeatability = ±17%

Average

Run #167

Run #168

Run #169

Run #170

-90 -60 -30 0 30 60 90 120 150 180

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 8 deg., M VD = 21 μm

Average Maximum β = 0.52

Repeatability = ±11%

Average

Run #184

Run #185

Run #186

Run #187

NASA/TM—2002-211700 175
 

Fig. 87 Test repeatability for commercial transport tail section - 1997 IRT tests.

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 4 deg., MVD = 92 μm

Average Maximum β = 0.74

Repeatab ility = ±9.8%

Average

Run #238

Run #239

Run #240

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper S urface | Lower S urface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., MVD = 11.5 μm

Average Maximum β = 0.47

Repeatability = ±9.6%

Average

Run #216

Run #217

Run #219

Run #244

Run #245

Run #246

-90 -60 -30 0 30 60 90 120 150 180

 <-- Up per S urface | L ower S urface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 4 deg., MVD = 21 μm

Average Maximum β = 0.54

Repeatability = ±7.0%

Average

Run #224

Run #225

Run #226

Run #227

Run #253

Run #254

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., MVD = 21 μm

Average Maximum β = 0.60

Repeatability = ±4.8%

 Average

Run #228

Run #229

Run #247

Run #248

Run #249

Run #251

Run #252

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., MVD = 92 μm

Average Maximum β = 0.76

Repeatability = ±9.2%

 Average

Run #233

Run #234

Run #235

Run #236

-90 -60 -30 0 30 60 90 120 150

 <-- Upper S urface | Lower S urface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 4 deg., MVD = 11.5 μm

Average Maximum β = 0.41

Repeatability = ±1.7%

Average

Run #220

Run #221

Run #223

NASA/TM—2002-211700 176
 

 

 

Fig. 88 Test repeatability for 36-in NLF(1)-0414 airfoil -1999 IRT tests. 

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., MVD = 11 μm

Average Maximum β = 0.45

Repeatability = ±5.3%

Average

Run #382B

Run #383B

Run #384B

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., MVD = 94 μm

Average Maximum β = 0.77

Repeatability = ±14%

Average

Run #394B

Run #395B

Run #396B

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., MVD = 21 μm

Average Maximum β = 0.60

Repeatability = ±0.24%

Average

Run #391B

Run #392B

Run #393B

-90 -60 -30 0 30 60 90 120 150 180

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 8 deg., MVD = 21 μm

Average Maxim um β = 0.57

R epeatability = ±2.3%

Average

Run #388B

Run #389B

Run #390B

-90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 8 deg., MVD = 11μm

Average Maximum β = 0.37

Repeatability = ±3.8%

Average

Run #385B

Run #386B

Run #387B

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 8 deg., MVD = 94 μm

Average Maximum β = 0.75

R epeatability = ±11%

Average

Run #397B

Run #398B

Run #399B

NASA/TM—2002-211700 177
 

 

Fig. 89a Test repeatability for 48-in NLF(1)-0414 airfoil -1999 IRT tests (Continued).

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., δ = 0 deg.

MVD = 94 μm

Average Maximum β = 0.75

Repeatability = ±8.1%

Average

Run #329B

Run #330B

Run #331B

Run #332B

-90 -60 -30 0 30 60 90 120 150 180

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 4 deg., δ = 0 deg.

MVD = 21 μm

Average Maximum β = 0.52

Repeatability = ±8.0%

Average

Run #368B

Run #369B

Run #370B

Run #371B

-90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 4 deg., δ = 0 deg.

MVD = 11μm

Average Maximum β = 0.38

Repeatability = ±4.6%

Average

Run #365B

Run #366B

Run #367B

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., δ = 0 deg.

MVD = 21 μm

Average Maximum β = 0.55

Repeatability = ±7.3%

Average

Run #350B

Run #351B

Run #352B

Run #353B

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., δ = 0 deg.

MVD = 11 μm

Average Maxim um β = 0.40

Repeatability = ±2.9%

Average

Run #333B

Run #334B

Run #335B

Run #336B

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 4 deg., δ = 0 deg.

MVD = 94 μm

Average Maxim um β = 0.72

Repeatability = ±0.8%

Average

Run #372B

Run #373B

Run #374B

NASA/TM—2002-211700 178
 

 

 

Fig. 89b Test repeatability for 48-in NLF(1)-0414 airfoil -1999 IRT tests.

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 8 deg., δ = 0 deg.

MVD = 94 μm

Average Maximum β = 0.70

Repeatability = ±6.2%

Average

Run #357B

Run #358B

Run #359B

Run #360B

-90 -60 -30 0 30 60 90 120 150 180

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 8 deg., δ = 0 deg.

MVD = 21 μm

Average Maximum β = 0.51

Repeatability = ±9.7%

Average

Run #354B

Run #355B

Run #356B

Run #361B

Run #362B

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., δ = 15 deg.

M VD = 94 μm

Average Maximum β = 0.75

Repeatability = ±11%

Average

Run #347B

Run #348B

Run #349B

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., δ = 15 deg.

MVD = 21 μm

Average Maximum β = 0.55

Repeatability = ±7.9%

Average

Run #344B

Run #345B

Run #346B

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., δ = 15 deg.

MVD = 11 μm

Average Maximum β = 0.41

Repeatability = ±5.9%

Average

Run #340B

Run #341B

Run #342B

-90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 8 deg., δ = 0 deg.

MVD = 11μm

Average Maximum β = 0.36

Repeatability = ±3.8%

Average

Run #337B

Run #338B

Run #339B

NASA/TM—2002-211700 179
 

 

Fig. 90 Test repeatability for NACA 64A008 swept tail -1997 IRT tests.

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α =6 deg., MVD = 92 μm

Average Maximum β = 0.70

Repeatability = ±3.2%

Average

Run #412

Run #413

Run #414

Run #415

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., MVD = 92 μm

Average Maximum β = 0.71

Repeatability = ±3.9%

Average

Run #409

Run #410

-90 -60 -30 0 30 60 90 120 150 180

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 6 deg., MVD = 21 μm

Average Maximum β = 0.61

Repeatability = ±8.2%

Average

Run #400

Run #401

Run #402

Run #403

-90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 6 deg., MVD = 11.5 μm

Average Maximum β = 0.45

Repeatability = ±12%

Average

Run #396

Run #397

Run #398

Run #399

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., MVD = 11.5 μm

Average Maximum β = 0.45

Repeatability = ±4.9%

Average

Run #393

Run #394

Run #395

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 0 deg., MVD = 21 μm

Average Maximum β = 0.61

Repeatability = ±7.4%

Average

Run #388

Run #405

Run #406

Run #407

NASA/TM—2002-211700 180
 

Fig. 91a Test repeatability for 25%-scale Business Jet Empennage 

1999 IRT tests; Inboard (Continued). 

-120 -90 -60 -30 0 30 60 90 120

 <-- Suction Su rface | Pressure Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = -1 deg., δ = 0 deg .

MVD = 11 μm, Inboard

A verage Maximum β = 0.60

R epeatability = ±4.0%

Average

Run #488B

Run #489B

pressure surface

suction surface

-90 -60 -30 0 30 60 90 120 150

 <-- S uction Su rface | P ressure S urface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = -6 deg., δ = 0 deg.

MVD = 11μm, Inboard

Average Maximum β = 0.59

Repeatability = ±4.9%

Average

Run #499B

Run #500B

Run #501B

pressure surface

suction surface

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- S uction S urface | P ressure S urface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = -6 deg., δ = 0 deg.

MVD = 94 μm, Inboard

Average Maximum β = 0.77

Repeatability = ±7.1%

Average

Run #496B

Run #497B

Run #498B

pressure surface

suction surface

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Suction Su rface | Pressure Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = -1 deg., δ = 0 deg.

MVD = 94 μm, Inboard

Average Maximum β = 0.80

Repeatability = ±5.9%

Average

Run #493B

Run #494B

Run #495B

pressure surface

suction surface

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Suction Su rface | Pressure Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = -1 deg., δ = 0 deg .

MVD = 21 μm, Inboard

A verage Maximum β = 0.70

R epeatability = ±6.2%

Average

Run #490B

Run #491B

Run #492B

pressure surface

suction surface

-90 -60 -30 0 30 60 90 120 150 180

 <-- S uction Su rface | P ressure S urface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = -6 deg., δ = 0 deg.

MVD = 21 μm, Inboard

Average Maximum β = 0.68

Repeatability = ±5.7%

Average

Run #502B

Run #503B

Run #504B

pressure surface

suction surface

NASA/TM—2002-211700 181
 

 

 

Fig. 91b Test repeatability for 25%-scale Business Jet Empennage 

1999 IRT tests; Outboard 

-90 -60 -30 0 30 60 90 120 150 180

 <-- S uction S urface | P ressure S urface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = -6 deg., δ = 0 deg.

MVD = 21 μm, Outboard

Average Maximum β = 0.71

Repeatability = ±4.6%

Average

Run #502A

Run #503A

Run #504A

pressure surface

suction surface

-90 -60 -30 0 30 60 90 120 150

 <-- S uction Su rface | P ressure S urface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = -6 deg., δ = 0 deg.

MVD = 11μm, Outboard

Average Maximum β = 0.62

Repeatability = ±3.4%

Average

Run #499A

Run #500A

Run #501A

pressure surface

suction surface

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- S uction S urface | P ressure S urface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = -6 deg., δ = 0 deg.

MVD = 94 μm, Outboard

Average Maximum β = 0.77

Repeatability = ±3.2%

Average

Run #496A

Run #497A

Run #498A

pressure surface

suction surface

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Suction Su rface | Pressure Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = -1 deg., δ = 0 deg.

MVD = 94 μm, Outboard

Average Maximum β = 0.81

Repeatability = ±3.7%

Average

Run #493A

Run #494A

Run #495A

pressure surface

suction surface

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Suction Surface | Pressure Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = -1 deg., δ = 0 deg.

MVD = 21 μm, Outboard

Average Maximum β = 0.73

Repeatability = ±14%

Average

Run #490A

Run #491A

Run #492A

pressure surface

suction surface

-120 -90 -60 -30 0 30 60 90 120

 <-- Suction Su rface | Pressure Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = -1 deg., δ = 0 deg.

MVD = 11 μm, Outboard

Average Maximum β = 0.62

Repeatability = ±4.8%

Average

Run #487A

Run #488A

Run #489A

pressure surface

suction surface

NASA/TM—2002-211700 182
 

 

Fig. 92a Test repeatability for full-scale Business Jet horizontal tail - 1999 IRT tests; 

 Inboard (Continued). 

-90 -60 -30 0 30 60 90 120 150 180

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 6 deg., δ = 0 deg.

MVD = 21 μm, Inboard

Average Maximum β = 0.57

Repeatability = ±8.7%

Average

Run #452A

Run #453A

Run #454A

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 1 deg., δ = 0 deg.

MVD = 21 μm, Inboard

Average Maximum β = 0.58

Repeatability = ±1.9%

Average

Run #443A

Run #444A

Run #445A

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 1 deg., δ = 0 deg.

MVD = 94 μm, Inboard

Average Maximum β = 0.72

Repeatability = ±8.5%

Average

Run #449A

Run #450A

Run #451A

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 1 deg., δ = 0 deg.

MVD = 11 μm, Inboard

Average Maximum β = 0.44

Repeatability = ±4.4%

Average

Run #446A

Run #447A

Run #448A

NASA/TM—2002-211700 183
 

 

Fig. 92b Test repeatability for full-scale Business Jet horizontal tail - 1999 IRT tests; 

 Outboard.

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 1 deg., δ = 0 deg.

MVD = 21 μm, Outboard

Average Maximum β = 0.61

Repeatability = ±2.4%

Average

Run #443B

Run #444B

Run #445B

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 1 deg., δ = 0 deg.

MVD = 94 μm, Outboard

Average Maximum β = 0.75

Repeatability = ±8.2%

Average

Run #449B

Run #450B

Run #451B

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 1 deg., δ = 0 deg.

MVD = 11 μm, Outboard

Average Maximum β = 0.46

Repeatability = ±1.6%

Average

Run #447B

Run #448B

-90 -60 -30 0 30 60 90 120 150 180

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

α = 6 deg., δ = 0 deg.

MVD = 21 μm, Outboard

Average Maximum β = 0.61

Repeatability = ±6.7%

Average

Run #452B

Run #453B

Run #454B

NASA/TM—2002-211700 184
Fig. 93a Test repeatability for three-element high lift system airfoil - 1997 IRT tests; 

 MVD = 11.5 

μm (Continued). 

-120 -90 -60 -30 0 30 60 90 120

<-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Slat Element

α = 0 deg., MVD = 11.5 μm

δslat = 30 deg. L.E. down

Average Maximum β = 0.35

Repeatability = ±7.7%

AverageRun #444Run #445Run #446Run #447Run #448Run #449

-150 -120 -90 -60 -30 0 30 60 90

<-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Slat Element

α = 4 deg., MVD = 11.5 μm

δslat = 30 deg. L. E. down

Average Maximum β = 0.35

Repeatability = ±11%

AverageRun #450Run #451Run #452Run #453

-90 -60 -30 0 30 60 90 120 150 180 210

<-- Upper Surface | Lower Surface --> Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Main Element

α = 0 deg., MVD = 11.5 μm

Average Maximum β = 0.05

Repeatability = ±17%

AverageRun #445Run #446Run #447Run #448

-90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface --> Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Main Element

α = 4 deg., MVD = 11.5 μm

Average Maximum β = 0.40

Repeatability = ±11%

AverageRun #450Run #451Run #452Run #453

-90 -60 -30 0 30 60 90 120 150 180

<-- Upper Surface | Lower Surface --> Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Flap Element

α = 0 deg., MVD = 11.5 μm

δflap = 30 deg. T. E. down

Average Maximum β = 0.29

Repeatability = ±10%

AverageRun #445Run #446Run #447Run #449

-90 -60 -30 0 30 60 90 120 150 180

<-- Upper Surface | Lower Surface --> Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Flap Element

α = 4 deg., MVD = 11.5 μm

δflap = 30 deg. T. E. down

Average Maximum β = 0.23

Repeatability = ±7.5%

AverageRun #450Run #451Run #452

NASA/TM—2002-211700 185
Fig. 93b Test repeatability for three-element high lift system airfoil - 1997 IRT tests; 

MVD = 21 

μm (Continued). 

-150 -120 -90 -60 -30 0 30 60 90 120 150

<-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Slat Element

α = 0 deg., MVD = 21 μm

δslat = 30 deg. L. E. down

Average Maximum β = 0.60

Repeatability = ±11%

AverageRun #458Run #459Run #460Run #461Run #462

-180 -150 -120 -90 -60 -30 0 30 60 90

<-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Slat Element

α = 4 deg., MVD = 21 μm

δslat = 30 deg. L. E. down

Average Maximum β = 0.64

Repeatability = ±9.4%

AverageRun #454Run #455Run #456Run #457

-90 -60 -30 0 30 60 90 120 150 180 210

<-- Upper Surface | Lower Surface -->  Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Main Element

α = 4 deg., MVD = 21 μm

Average Maximum β = 0.38

Repeatability = ±5.6%

AverageRun #454Run #455Run #456Run #457

-90 -60 -30 0 30 60 90 120 150 180 210 240 270

<-- Upper Surface | Lower Surface --> Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Main Element

α = 0 deg., MVD = 21 μm

Average Maximum β = 0.05

Repeatability = ±17%

AverageRun #458Run #459Run #461Run #462

-90 -60 -30 0 30 60 90 120 150 180 210

<-- U pper S urface | Lower S urface --> Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Flap Element

α = 0 deg., MVD = 21 μm

δflap = 30 deg. T. E. down

Average Maximum β = 0.51

Repeatability = ±10%

AverageRun #458Run #460Run #461Run #462

-90 -60 -30 0 30 60 90 120 150 180 210

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Flap Element

α = 4 deg., MVD = 21 μm

δflap = 30 deg. T. E. down

Average Maximum β = 0.53

Repeatability = ±8.5%

AverageRun #454Run #455Run #456Run #457

NASA/TM—2002-211700 186
Fig. 93c Test repeatability for three-element high lift system airfoil - 1997 IRT tests; 

MVD = 92 

μm. 

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

<-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Slat Element

α = 0 deg., MVD = 92 μm

δslat = 30 deg. L. E. down

Average Maximum β = 0.84

Repeatability = ±9.2%

AverageRun #463Run #464Run #465Run #466

-270 -240 -210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150

<-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Slat Element

α = 4 deg., MVD = 92 μmδslat = 30 deg. L. E. down

Average Maximum β = 0.82

Repeatability = ±16%

AverageRun #467Run #468Run #469Run #470

-60 -30 0 30 60 90 120 150 180 210 240 270 300

<-- Upper Surface | Lower Surface --> Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Main Element

α = 4 deg., MVD = 92 μm

Average Maximum β = 0.30

Repeatability = ±9.5%

AverageRun #467Run #468Run #469Run #470

-60 -30 0 30 60 90 120 150 180 210 240 270 300

<-- Upper Surface | Lower Surface --> Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Main Element

α = 0 deg., MVD = 92 μm

Average Maximum β = 0.04

Repeatability = N/A

AverageRun #458Run #459Run #461Run #462

-90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

<-- U pp er S urface | L ower S urface -->

 Surface Distance from Highlight (mm)

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Flap Element

α = 0 deg., MVD = 92 μm

δflap = 30 deg. T. E. down

Average Maximum β = 0.74

Repeatability = ±8.6%

AverageRun #463Run #464Run #465Run #466

-90 -60 -30 0 30 60 90 120 150 180 210 240 270

<-- U pper S urface | Lo wer S urface --> Surface Distance from Highlight (mm)

0

0.90.80.70.60.50.40.30.20.1

1

) β Local Impingement Efficiency (

Flap Element

α = 4 deg., MVD = 92 μm

δflap = 30 deg. T. E. down

Average Maximum β = 0.78

Repeatability = ±15%

AverageRun #467Run #469Run #470

NASA/TM—2002-211700 187
 

 

 

Fig. 94 Test repeatability for S-duct engine inlet - 1999 IRT tests; V∞ = 170 mph, 

capture area ratio = 0.65, mass flow rate = 23 lbm/sec. 

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180

 <-- Inner Surface | Outer Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

MVD = 94 μm, Location A

Average Maximum β = 0.58

Repeatability = ±11%

Average

Run #536A

Run #537A

Run #538A

-180 -150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Inner Surface | Outer Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

MVD = 21 μm, Location A

Average Maximum β = 0.49

R epeatability = ±4.6%

Average

Run #539A

Run #540A

Run #541A

-150 -120 -90 -60 -30 0 30 60 90 120

 <-- Inner Surface | Outer Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

MVD = 11 μm, Location A

Average Maximum β = 0.36

Repeatability = ±6.8%

Average

Run #548A

Run #549A

Run #550A

location A

-30 0 30 60 90 120 150 180 210 240 270 300

Air Flow →

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

MVD = 94 μm , Location B

Average Maximum β = 0.253

Repeatability = ±12%

Average

Run #536B

Run #537B

Run #538B

-30 0 30 60 90 120 150 180 210 240 270

Air Flow →

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

MVD = 21 μm, Location B

Average Maximum β = 0.080

Repeatability = ±13%

Average

Run #539B

Run #540B

Run #541B

-30 0 30 60 90 120 150 180 210 240

A ir Flow →

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

MVD = 11 μm, Location B

Average Maximum β = 0.006

Repeatability = N/A

Average

Run #548B

Run #549B

Run #550B

NASA/TM—2002-211700 188
Fig. 95a Impingement efficiency distribution for MS(1)-0317 airfoil; 

1997 IRT tests, c = 36-in, V∞ = 176 mph, α=0°, MVD =11.5 μm (Continued). 

-120 -90 -60 -30 0 30 60 90 120

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

MS(1)-317 Airfoil

α = 0 deg., MVD = 11.5 μm

Analysis (LEWICE)

Test Data (Laser System)

Test Data (CCD Camera)

βmax= 0.32 at S = -6 mm

Area of β curve per unit span = 11.09 mm2

Total Impingement Efficiency = 0.071

Exp. Impingement Limits:

Upper Surface = -71 mm

Lower Surface = +30 mm

NASA/TM—2002-211700 189
Fig. 95b Impingement efficiency distribution for MS(1)-0317 airfoil; 

1997 IRT tests, c = 36-in, V∞ = 176 mph, α=0°, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

MS(1)-317 Airfoil

α = 0 deg., MVD = 21 μm

Analysis (LEWICE)

Test Data (Laser System)

Test Data (CCD Camera)

Exp. Impingement Limits:

Upper Surface = -90 mm

Lower Surface = +45 mm

βmax= 0.50 at S = -1 mm

Area of β curve per unit span = 26.43 mm2

Total Impingement Efficiency = 0.170

NASA/TM—2002-211700 190
Fig. 95c Impingement efficiency distribution for MS(1)-0317 airfoil; 

1997 IRT tests, c = 36-in, V∞ = 176 mph, α=0°, MVD =92 μm (Continued).

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

MS(1)-0317 Airfoil

α = 0 deg., MVD = 92 μm

Analysis (LEWICE)

Test Data

(Laser System)

Test Data

(CCD Camera)

Exp. Impingement Limits:

Upper Surface = -240 mm 

Lower Surface = +149 mm

βmax= 0.68 at S = -4 mm

Area of β curve per unit span = 49.53 mm2

Total Impingement Efficiency = 0.319

NASA/TM—2002-211700 191
Fig. 95d Impingement efficiency distribution for MS(1)-0317 airfoil; 

1997 IRT tests, c = 36-in, V∞ = 176 mph, α=8°, MVD =11.5 μm (Continued).

-90 -60 -30 0 30 60 90 120 150

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

MS(1)-0317 Airfoil

α = 8 deg., MVD = 11.5 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -15 mm

Lower Surface = +66 mm

βmax= 0.25 at S = +16 mm

Area of β curve per unit span = 7.69 mm2

Total Impingement Efficiency = 0.041

NASA/TM—2002-211700 192
Fig. 95e Impingement efficiency distribution for MS(1)-0317 airfoil; 

1997 IRT tests, c = 36-in, V∞ = 176 mph, α=8°, MVD =21 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

MS(1)-317 Airfoil

α = 8 deg., MVD = 21 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -34 mm

Lower Surface = +185 mm

βmax= 0.51 at S = +12 mm

Area of β curve per unit span = 33.43 mm2

Total Impingement Efficiency = 0.179

NASA/TM—2002-211700 193
Fig. 95f Impingement efficiency distribution for MS(1)-0317 airfoil; 

1997 IRT tests, c = 36-in, V∞ = 176 mph, α=8°, MVD =92 μm.

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

MS(1)-317 Airfoil

α = 8 deg., MVD = 92 μm

Analysis (LEWICE)

Test Data

(Laser System)

Exp. Impingement Limits:

Upper Surface = -60 mm

Lower Surface = +300 mm

βmax= 0.76 at S = +8 mm

Area of β curve per unit span = 67.41 mm2

Total Impingement Efficiency = 0.361

NASA/TM—2002-211700 194
Fig. 96a Impingement efficiency distribution for MS(1)-0317 airfoil; 

1999 IRT tests, c = 36-in, V∞ = 176 mph, α=0°, MVD =11 μm (Continued).

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

MS(1)-317 Airfoil

α = 0 deg., MVD = 11 μm

Analysis (LEWICE)

Test Data (Laser System)

Test Data (CCD Camera)

Exp. Impingement Limits:

Upper Surface = -62 mm

Lower Surface = +30 mm

βmax= 0.33 at S = -6 mm

Area of β curve per unit span = 12.08 mm 2

Total Impingement Efficiency = 0.078

NASA/TM—2002-211700 195
Fig. 96b Impingement efficiency distribution for MS(1)-0317 airfoil; 

1999 IRT tests, c = 36-in, V∞ = 176 mph, α=0°, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

MS(1)-317 Airfoil

α = 0 deg., MVD = 21 μm

Analysis (LEWICE)

Test Data (Laser System)

Test Data (CCD Camera)

Exp. Impingement Limits:

Upper Surface = -89 mm

Lower Surface = +63 mm

βmax= 0.50 at S = 0 mm

Area of β curve per unit span = 29.84 mm2

Total Impingement Efficiency = 0.192

NASA/TM—2002-211700 196
Fig. 96c Impingement efficiency distribution for MS(1)-0317 airfoil; 

1999 IRT tests, c = 36-in, V∞ = 176 mph, α=0°, MVD =94 μm.

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

MS(1)-0317 Airfoil

α = 0 deg., MV D = 94 μm

Analysis (LEWICE)

Test Data

(Laser System)

Test Data

(CCD Camera)

Exp. Impingement Limits:

Upper Surface = -164 mm

Lower Surface = +117 mm

βmax= 0.68 at S = -2 mm

Area of β curve per unit span = 50.17 mm 2

Total Impingement Efficiency = 0.322

NASA/TM—2002-211700 197
Fig. 97a Comparison of 1997 and 1999 impingement efficiency test results for 

MS(1)-0317 airfoil; c = 36-in, V∞ = 176 mph, α=0°, MVD =11, 11.5 μm. (Continued). 

-120 -90 -60 -30 0 30 60 90 120

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

MS(1)-317 Airfoil

α = 0 deg., MVD = 11,11.5 μm

Analysis (LEWICE)

1997 Test Data (Laser System)

1999 Test Data (Laser System)

NASA/TM—2002-211700 198
Fig. 97b Comparison of 1997 and 1999 impingement efficiency test results for 

MS(1)-0317 airfoil; c = 36-in, V∞ = 176 mph, α=0°, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

MS(1)-317 Airfoil

α = 0 deg., MVD = 21 μm

Analysis (LEWICE)

1997 Test Data (Laser System)

1999 Test Data (Laser System)

NASA/TM—2002-211700 199
Fig. 97c Comparison of 1997 and 1999 impingement efficiency test results for 

MS(1)-0317 airfoil; c = 36-in, V∞ = 176 mph, α=0°, MVD =92, 94 μm.

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

MS(1)-0317 Airfoil

α = 0 deg., MVD = 92, 94 μm

Analysis (LEWICE)

1997 Test Data

(Laser System)

1999 Test Data

(Laser System)

NASA/TM—2002-211700 200
Fig. 98a Impingement efficiency distribution for GLC-305 airfoil; 

 c = 36-in, V∞ = 176 mph, α=1.5°, MVD =11.5 μm (Continued). 

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

GLC 305 Airfoil

α = 1.5 deg., MVD = 11.5 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -26 mm

Lower Surface = +34 mm

βmax= 0.0.47 at S = +1 mm

Area of β curve per unit span = 9.25 mm2

Total Impingement Efficiency = 0.117

NASA/TM—2002-211700 201
Fig. 98b Impingement efficiency distribution for GLC-305 airfoil; 

c = 36-in, V∞ = 176 mph, α=1.5°, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

GLC 305 Airfoil

α = 1.5 deg., MVD = 21 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -42 mm

Lower Surface = +55 mm

βmax= 0.66 at S = +2 mm

Area of β curve per unit span = 16.34 mm2

Total Impingement Efficiency = 0.206

NASA/TM—2002-211700 202
Fig. 98c Impingement efficiency distribution for GLC-305 airfoil; 

 c = 36-in, V∞ = 176 mph, α=1.5°, MVD =92 μm (Continued).

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

GLC 305 Airfoil

α = 1.5 deg., MVD = 92 μm

Analysis (LEWICE)

Test Data

(Laser System)

Exp. Impingement Limits:

Upper Surface = -153 ++ mm

Lower Surface = +229 ++ mm

++ end of blotter strip

βmax= 0.76 at S = +2 mm

Area of β curve per unit span = 26.08 mm2

Total Impingement Efficiency = 0.328

NASA/TM—2002-211700 203
Fig. 98d Impingement efficiency distribution for GLC-305 airfoil; 

c = 36-in, V∞ = 176 mph, α=6°, MVD =11.5 μm (Continued).

-90 -60 -30 0 30 60 90 120 150

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

GLC 305 Airfoil

α = 6 deg., MVD = 11.5 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -14 mm

Lower Surface = +60 mm

βmax= 0.43 at S = +6 mm

Area of β curve per unit span = 8.96 mm2

Total Impingement Efficiency = 0.078

NASA/TM—2002-211700 204
Fig. 98e Impingement efficiency distribution for GLC-305 airfoil; 

 c = 36-in, V∞ = 176 mph, α=6°, MVD =21 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

GLC 305 Airfoil

α = 6 deg., MVD = 21 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -22 mm

Lower Surface = +322 mm

βmax= 0.60 at S = +6 mm

Area of β curve per unit span = 25.81 mm 2

Total Impingement Efficiency = 0.224

NASA/TM—2002-211700 205
Fig. 98f Impingement efficiency distribution for GLC-305 airfoil; 

 c = 36-in, V∞ = 176 mph, α=6°, MVD =92 μm.

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

GLC 305 Airfoil

α = 6 deg., MVD = 92 μm

Analysis (LEWICE)

Test Data

(Laser System)

Exp. Impingement Limits:

Upper Surface = -25 mm

Lower Surface = +526 mm

βmax= 0.72at S = +4 mm

Area of β curve per unit span = 46.75 mm2

Total Impingement Efficiency = 0.406

NASA/TM—2002-211700 206
Fig. 99a Impingement efficiency distribution for NACA 652-415 airfoil; 

 c = 36-in, V∞ = 176 mph, α=0°, MVD =11.5 μm (Continued). 

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NACA 652-415 Airfoil

α = 0 deg., MVD = 11.5 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limit:

Upper Surface = -48 mm

Lower Surface = +40 mm

βmax= 0.45 at S = +1 mm

Area of β curve per unit span = 8.26 mm 2

Total Impingement Efficiency = 0.059

NASA/TM—2002-211700 207
Fig. 99b Impingement efficiency distribution for NACA 652-415 airfoil; 

c = 36-in, V∞ = 176 mph, α=0°, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NACA 652-415 Airfoil

α = 0 deg., MVD = 21 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -140 mm

Lower Surface = +75 mm

βmax= 0.62 at S = 0 mm

Area of β curve per unit span = 19.51 mm 2

Total Impingement Efficiency = 0.140

NASA/TM—2002-211700 208
Fig. 99c Impingement efficiency distribution for NACA 652-415 airfoil; 

c = 36-in, V∞ = 176 mph, α=0°, MVD =92 μm (Continued).

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NACA 652-415 Airfoil

α = 0 deg., MVD = 92 μm

Analysis (LEWICE)

Test Data

(Laser System)

Exp. Impingement Limits:

Upper Surface = -195 mm

Lower Surface = +150 mm

βmax= 0.73 at S = -2 mm

Area of β curve per unit span = 36.48 mm 2

Total Impingement Efficiency = 0.262

NASA/TM—2002-211700 209
Fig. 99d Impingement efficiency distribution for NACA 652-415 airfoil; 

c = 36-in, V∞ = 176 mph, α=8°, MVD =11.5 μm (Continued).

-90 -60 -30 0 30 60 90 120 150

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NACA 652-415 Airfoil

α = 8 deg., MVD = 11.5 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -15 mm

Lower Surface = +135 mm

βmax= 0.30 at S = +11 mm

Area of β curve per unit span = 7.90 mm 2

Total Impingement Efficiency = 0.045

NASA/TM—2002-211700 210
Fig. 99e Impingement efficiency distribution for NACA 652-415 airfoil; 

c = 36-in, V∞ = 176 mph, α=8°, MVD =21 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NACA 652-415 Airfoil

α = 8 deg., MVD = 21 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -20 mm

Lower Surface = +227 mm

βmax= 0.52 at S = +11 mm

Area of β curve per unit span = 22.04 mm 2

Total Impingement Efficiency = 0.125

NASA/TM—2002-211700 211
Fig. 99f Impingement efficiency distribution for NACA 652-415 airfoil; 

c = 36-in, V∞ = 176 mph, α=8°, MVD =92 μm.

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NACA 652-415 Airfoil

α = 8 deg., MVD = 92 μm

Analysis (LEWICE)

Test Data

(Laser System)

Exp. Impingement Limits:

Upper Surface = -100 ++ mm

Lower Surface = +407 ++ mm

++ end of blotter strip

βmax= 0.69 at S = +8 mm

Area of β curve per unit span = 61.63 mm 2

Total Impingement Efficiency = 0.351

NASA/TM—2002-211700 212
Fig. 100a Impingement efficiency distribution for commercial transport tail section; 

c = 36-in, V∞ = 176 mph, α=0°, MVD =11.5 μm (Continued). 

-120 -90 -60 -30 0 30 60 90 120

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Commercial Transport

Tail Section

α = 0 deg., MVD = 11.5 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -41 mm

Lower Surface = +25 mm

βmax= 0..47 at S = -1 mm

Area of β curve per unit span = 9.05 mm2

Total Impingement Efficiency = 0.110

NASA/TM—2002-211700 213
Fig. 100b Impingement efficiency distribution for commercial transport tail section; 

c = 36-in, V∞ = 176 mph, α=0°, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Commercial Transport

Tail Section

α = 0 deg., MVD = 21 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -82 mm

Lower Surface = +52 mm

βmax= 0.60 at S = -1 mm

Area of β curve per unit span = 17.76 mm 2

Total Impingement Efficiency = 0.217

NASA/TM—2002-211700 214
Fig. 100c Impingement efficiency distribution for commercial transport tail section; 

c = 36-in, V∞ = 176 mph, α=0°, MVD =92 μm (Continued).

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Commercial Transport

Tail Section

α = 0 deg., MVD = 92 μm

Analysis (LEWICE)

Test Data

(Laser System)

Exp. Impingement Limits:

Upper Surface = -130 mm

Lower Surface = +100 mm

βmax= 0.76 at S = -1 mm

Area of β curve per unit span = 29.81 mm 2

Total Impingement Efficiency = 0.363

NASA/TM—2002-211700 215
Fig. 100d Impingement efficiency distribution for commercial transport tail section; 

c = 36-in, V∞ = 176 mph, α=4°, MVD =11.5 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180

<-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Commercial Transport

Tail Section

α = 4 deg., MVD = 11.5 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -23 mm

Lower Surface = +55 mm

βmax= 0.41 at S = +4 mm

Area of β curve per unit span = 8.96 mm2

Total Impingement Efficiency = 0.091

NASA/TM—2002-211700 216
Fig. 100e Impingement efficiency distribution for commercial transport tail section; 

c = 36-in, V∞ = 176 mph, α=4°, MVD =21 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180

 <-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Commercial Transport

Tail Section

α = 4 deg., MVD = 21 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -40 mm

Lower Surface = +175 mm

βmax= 0.54 at S = +4 mm

Area of β curve per unit span = 19.03 mm2

Total Impingement Efficiency = 0.192

NASA/TM—2002-211700 217
Fig. 100f Impingement efficiency distribution for commercial transport tail section; 

c = 36-in, V∞ = 176 mph, α=4°, MVD =92 μm.

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Commercial Transport

Tail Section

α = 4 deg., MVD = 92 μm

Analysis (LEWICE)

Test Data

(Laser System)

Exp. Impingement Limits:

Upper Surface = -80 mm

Lower Surface = +371 ++ mm

++ end of blotter strip

βmax= 0.74 at S = +2 mm

Area of β curve per unit span = 42.06 mm2

Total Impingement Efficiency = 0.425

NASA/TM—2002-211700 218
Fig. 101a Impingement efficiency distribution for NLF(1)-0414 airfoil; 

c = 36-in, V∞ = 176 mph, α=0°, MVD =11 μm (Continued). 

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 0 deg., MVD = 11 μm

C hord Length = 36"

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -35 mm

Lower Surface = +33 mm

βmax= 0.45 at S = -3 mm

Area of β curve per unit span = 9.71 mm2

Total Impingement Efficiency = 0.074

NASA/TM—2002-211700 219
Fig. 101b Impingement efficiency distribution for NLF(1)-0414 airfoil; 

c = 36-in, V∞ = 176 mph, α=0°, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 0 deg., MVD = 21 μm

C hord Length = 36"

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -76 mm

Lower Surface = +79 mm

βmax= 0.60 at S = -2 mm

Area of β curve per unit span = 20.45 mm2

Total Impingement Efficiency = 0.157

NASA/TM—2002-211700 220
Fig. 101c Impingement efficiency distribution for NLF(1)-0414 airfoil; 

c = 36-in, V∞ = 176 mph, α=0°, MVD =94 μm (Continued).

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 0 deg., MVD = 94 μm

Chord Length = 36"

Analysis

(LEWICE)

Test Data

(Laser System)

Exp. Impingement Limits:

Upper Surface = -230 ++ mm

Lower Surface = +180 mm

βmax= 0.77 at S = -2 mm

Area of β curve per unit span = 35.26 mm2

Total Impingement Efficiency = 0.270

++ end of blotter strip

NASA/TM—2002-211700 221
Fig. 101d Impingement efficiency distribution for NLF(1)-0414 airfoil; 

c = 36-in, V∞ = 176 mph, α=8°, MVD =11 μm (Continued).

-90 -60 -30 0 30 60 90 120 150

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 8 deg., MVD = 11 μm

C hord Length = 36"

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -22 mm

Lower Surface = +100 mm

βmax= 0.37 at S = +5 mm

Area of β curve per unit span = 10.79 mm2

Total Impingement Efficiency = 0.057

NASA/TM—2002-211700 222
Fig. 101e Impingement efficiency distribution for NLF(1)-0414 airfoil; 

c = 36-in, V∞ = 176 mph, α=8°, MVD =21 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180

<-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 8 deg., MVD = 21 μm

C hord Length = 36"

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -20 mm

Lower Surface = +400 mm

βmax= 0.57 at S = +8 mm

Area of β curve per unit span = 36.85 mm2

Total Impingement Efficiency = 0.195

NASA/TM—2002-211700 223
Fig. 101f Impingement efficiency distribution for NLF(1)-0414 airfoil; 

c = 36-in, V∞ = 176 mph, α=8°, MVD =94 μm.

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 8 deg., MVD = 94 μm

C hord Length = 36"

Analysis

(LEWICE)

Test Data

(Laser System)

Exp. Impingement Limit:

Upper Surface = -30 mm

Lower Surface = +465 ++ mm

βmax= 0.75 at S = +8 mm

Area of β curve per unit span = 61.48 mm 2

Total Impingement Efficiency = 0.324

++ end of blotter strip

NASA/TM—2002-211700 224
Fig. 102a Impingement efficiency distribution for NLF(1)-0414 airfoil; c = 48-in, 

25%-chord full-span flap, V∞ = 176 mph, α=0°, δ=0°, MVD =11 μm (Continued). 

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 0 deg., δ = 0 deg., MVD = 11 μm

Chord Length = 48"

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -35mm

Lower Surface = +45 mm

βmax= 0.40 at S = -2 mm

Area of β curve per unit span = 10.32 mm2

Total Impingement Efficiency = 0.059

NASA/TM—2002-211700 225
Fig. 102b Impingement efficiency distribution for NLF(1)-0414 airfoil; c = 48-in, 

25%-chord full-span flap, V∞ = 176 mph, α=0°, δ=0°, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 0 deg., δ = 0 deg., MVD = 21 μm

Chord Length = 48"

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -95 mm

Lower Surface = +84 mm

βmax= 0.55 at S = -2 mm

Area of β curve per unit span = 22.81 mm 2

Total Impingement Efficiency = 0.131

NASA/TM—2002-211700 226
Fig. 102c Impingement efficiency distribution for NLF(1)-0414 airfoil; c = 48-in, 

 25%-chord full-span flap, V∞ = 176 mph, α=0°, δ=0°, MVD =94 μm (Continued).

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 0 deg., δ = 0 deg.

MVD = 94 μm

Chord Length = 48"

Analysis

(LEWICE)

Test Data

(Laser System)

Exp. Impingement Limits:

Upper Surface = -200 mm

Lower Surface = +180 mm

βmax= 0.75 at S = -2 mm

Area of β curve per unit span = 44.98 mm2

Total Impingement Efficiency = 0.259

NASA/TM—2002-211700 227
Fig. 102d Impingement efficiency distribution for NLF(1)-0414 airfoil; c = 48-in, 

25%-chord full-span flap, V∞ = 176 mph, α=4°, δ=0°, MVD =11 μm (Continued).

-90 -60 -30 0 30 60 90 120 150

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 4 deg., δ = 0 deg., MVD = 11 μm

C hord Length = 48"

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -25 mm

Lower Surface = +65 mm

βmax= 0.38 at S = +10 mm

Area of β curve per unit span = 10.19 mm2

Total Impingement Efficiency = 0.053

NASA/TM—2002-211700 228
Fig. 102e Impingement efficiency distribution for NLF(1)-0414 airfoil; c = 48-in, 

25%-chord full-span flap, V∞ = 176 mph, α=4°, δ=0°, MVD =21 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180

<-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 4 deg., δ = 0 deg., MVD = 21 μm

C hord Length = 48"

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -40 mm

Lower Surface = +340 mm

βmax= 0.52 at S = +8 mm

Area of β curve per unit span = 31.46 mm 2

Total Impingement Efficiency = 0.162

NASA/TM—2002-211700 229
Fig. 102f Impingement efficiency distribution for NLF(1)-0414 airfoil; c = 48-in, 

25%-chord full-span flap, V∞ = 176 mph, α=4°, δ=0°, MVD =94 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 4 deg., δ = 0 deg., MVD = 94 μm

C hord Length = 48"

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -60 mm

Lower Surface = +446 mm

βmax= 0.72 at S = +7 mm

Area of β curve per unit span = 55.71 mm2

Total Impingement Efficiency = 0.288

NASA/TM—2002-211700 230
Fig. 102g Impingement efficiency distribution for NLF(1)-0414 airfoil; c = 48-in, 

25%-chord full-span flap, V∞ = 176 mph, α=8°, δ=0°, MVD =11 μm (Continued).

-90 -60 -30 0 30 60 90 120 150

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 8 deg., δ = 0 deg., MVD = 11 μm

Chord Length = 48"

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -10 mm

Lower Surface = +98 mm

βmax= 0.36 at S = +16 mm

Area of β curve per unit span = 11.22 mm2

Total Impingement Efficiency = 0.044

NASA/TM—2002-211700 231
Fig. 102h Impingement efficiency distribution for NLF(1)-0414 airfoil; c = 48-in, 

25%-chord full-span flap, V∞ = 176 mph, α=8°, δ=0°, MVD =21 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180

<-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 8 deg., δ = 0 deg., MVD = 21 μm

Chord Length = 48"

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -28 mm

Lower Surface = +370 mm

βmax= 0.51 at S = +11 mm

Area of β curve per unit span = 36.87 mm2

Total Impingement Efficiency = 0.146

NASA/TM—2002-211700 232
Fig. 102i Impingement efficiency distribution for NLF(1)-0414 airfoil; c = 48-in, 

25%-chord full-span flap, V∞ = 176 mph, α=8°, δ=0°, MVD =94 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 8 deg., δ = 0 deg., MVD = 94 μm

C hord Length = 48"

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -42 mm

Lower Surface = +750 mm

βmax= 0.70 at S = +7 mm

Area of β curve per unit span = 78.30 mm2

Total Impingement Efficiency = 0.310

NASA/TM—2002-211700 233
Fig. 102j Impingement efficiency distribution for NLF(1)-0414 airfoil; c =48-in, 

25%-chord full-span flap, V∞ = 176 mph, α=0°, δ=15°, MVD =11 μm (Continued).

-120 -90 -60 -30 0 30 60 90 120

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 0 deg., δ = 15 deg., MVD = 11 μm

C hord Length = 48"

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -33 mm**

Lower Surface = +70 mm**

** impingement properties on 

 the main element only. Blue 

 dye was observed again on 

 the lower surface of the flap 

 element (near the end of the 

 blotter strip at surface distance

 +1049 mm ~ +1131 mm). The 

 impingement efficiency of the

 flap element near the trailling

 edge can be found in the next 

 graph.

βmax= .41 at S = +7 mm

Area of β curve per unit span = 12.13** mm2

Total Impingement Efficiency = 0.057**

NASA/TM—2002-211700 234
Fig. 102k Impingement efficiency distribution for NLF(1)-0414 flap element; c =48-in, 

25%-chord full-span flap, V∞ = 176 mph, α=0°, δ=15°, MVD =11 μm (Continued).

900 930 960 990 1020 1050 1080 1110 1140 1170 1200

<-- Highlight | Trailing Edge -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

Flap Element

(Lower Surface)

α = 0 deg., δ = 15 deg., MVD = 11 μm

Chord Length = 48"

Test Data (Laser System)

NASA/TM—2002-211700 235
Fig. 102l Impingement efficiency distribution for NLF(1)-0414 airfoil; c =48-in, 

25%-chord full-span flap, V∞ = 176 mph, α=0°, δ=15°, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 0 deg., δ = 15 deg., MVD = 21 μm

Chord Length = 48"

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -50 mm**

Lower Surface = +180 mm**

βmax= 0.55 at S = +8 mm

Area of β curve per unit span = 27.29** mm 2

Total Impingement Efficiency = 0.129**

** impingement properties on 

 the main element only. Blue 

 dye was observed again on 

 the lower surface of the flap 

 element (near the end of the 

 blotter strip at surface distance

 +1092 mm ~ +1186 mm). The 

 impingement efficiency of the

 flap element near the trailling

 edge can be found in the next 

 graph.

NASA/TM—2002-211700 236
Fig. 102m Impingement efficiency distribution for NLF(1)-0414 flap element; c =48-in, 

25%-chord full-span flap, V∞ = 176 mph, α=0°, δ=15°, MVD =21 μm (Continued).

900 930 960 990 1020 1050 1080 1110 1140 1170 1200

<-- Highlight | Trailing Edge -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

Flap Element

(Lower Surface)

α = 0 deg., δ = 15 deg., MVD = 21 μm

Chord Length = 48"

Test Data (Laser System)

NASA/TM—2002-211700 237
Fig. 102n Impingement efficiency distribution for NLF(1)-0414 airfoil; c =48-in, 

25%-chord full-span flap, V∞ = 176 mph, α=0°, δ=15°, MVD =94 μm (Continued).

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

α = 0 deg., δ = 15 deg.

MVD = 94 μm

C hord Length = 48"

Analysis

(LEWICE)

Test Data

(Laser System)

Exp. Impingement Limits:

Upper Surface = -110 mm**

Lower Surface = +300 mm**

βmax= 0.75 at S = +6 mm

Area of β curve per unit span = 51.81** mm2

Total Impingement Efficiency = 0.244**

** impingement properties on 

 the main element only. Blue 

 dye was observed again on 

 the lower surface of the flap 

 element (near the end of the 

 blotter strip at surface distance

 +1059 mm ~ +1191 mm). The 

 impingement efficiency of the

 flap element near the trailling

 edge can be found in the next 

 graph.

NASA/TM—2002-211700 238
Fig. 102o Impingement efficiency distribution for NLF(1)-0414 flap element; 

c =48-in, 25%-chord full-span flap, V∞ = 176 mph, α=0°, δ=15°, MVD =94 μm. 

900 930 960 990 1020 1050 1080 1110 1140 1170 1200

<-- Highlight | Trailing Edge -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NLF(1)-0414 Airfoil

Flap Element

(Lower Surface)

α = 0 deg., δ = 15 deg., MVD = 94 μm

Chord Length = 48"

Test Data (Laser System)

NASA/TM—2002-211700 239
Fig. 103a Impingement efficiency distribution for NACA 64A008 finite swept tail; 

c = 45.75-in, V∞ = 176 mph, α=0°, MVD =11.5 μm (Continued). 

-120 -90 -60 -30 0 30 60 90 120

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NACA 64A008 Finite Swept Tail

α = 0 deg., MVD = 11.5 μm, Inboard

Analysis (LEWICE3D, Inboard)

Analysis (LEWICE3D, Outboard)

Test Data (Laser System)

Exp. Impingement Limit:

Upper Surface = -25 mm

Lower Surface = +25 mm

βmax= 0.45 at S = 0 mm

Area of β curve per unit span = 5.97 mm2

Total Impingement Efficiency = 0.078

NASA/TM—2002-211700 240
Fig. 103b Impingement efficiency distribution for NACA 64A008 finite swept tail; 

c = 45.75-in, V∞ = 176 mph, α=0°, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NACA 64A008 Finite Swept Tail

α = 0 deg., MVD = 21 μm, Inboard

Analysis (LEWICE3D, Inboard)

Analysis (LEWICE3D, Outboard)

Test Data (Laser System)

Exp. Impingement Limit:

Upper Surface = -80 mm

Lower Surface = +80 mm

βmax= 0.61 at S = +2 mm

Area of β curve per unit span = 13.86 mm2

Total Impingement Efficiency = 0.181

NASA/TM—2002-211700 241
Fig. 103c Impingement efficiency distribution for NACA 64A008 finite swept tail; 

 c = 45.75-in, V∞ = 176 mph, α=0°, MVD =92 μm (Continued).

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NACA 64A008 

Finite Swept Tail

α = 0 deg., MVD = 92 μm ,

Inboard

Analysis

(LEWICE3D, Inboard)

Analysis

(LEWICE3D, Outboard)

Test Data

(Laser System)

Exp. Impingement Limit:

Upper Surface = -180 mm

Lower Surface = +180 mm

βmax= 0.71 at S = 0 mm

Area of β curve per unit span = 23.08 mm 2

Total Impingement Efficiency = 0.302

NASA/TM—2002-211700 242
Fig. 103d Impingement efficiency distribution for NACA 64A008 finite swept tail; 

 c = 45.75-in, V∞ = 176 mph, α=6°, MVD =11.5 μm (Continued).

-90 -60 -30 0 30 60 90 120 150

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NACA 64A008 Finite Swept Tail

Inboard

α = 6 deg., MVD = 11.5 μm

Analysis (LEWICE3D, Inboard)

Analysis (LEWICE3D, Outboard)

Test Data (Laser System)

Exp. Impingement Limit:

Upper Surface = -5 mm

Lower Surface = +80 mm

βmax= 0.45 at S = +6 mm

Area of β curve per unit span = 8.789 mm2

Total Impingement Efficiency = 0.076

NASA/TM—2002-211700 243
Fig. 103e Impingement efficiency distribution for NACA 64A008 finite swept tail; 

 c = 45.75-in, V∞ = 176 mph, α=6°, MVD =21 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NACA 64A008 Finite Swept Tail

Inboard

α = 6 deg., MVD = 21 μm

Analysis (LEWICE3D, Inboard)

Analysis (LEWICE3D, Outboard)

Test Data (Laser System)

Exp. Impingement Limit:

Upper Surface = -10 mm

Lower Surface = +310 mm

βmax= 0.61 at S = +5 mm

Area of β curve per unit span = 26.23 mm 2

Total Impingement Efficiency = 0.226

NASA/TM—2002-211700 244
Fig. 103f Impingement efficiency distribution for NACA 64A008 finite swept tail; 

 c = 45.75-in, V∞ = 176 mph, α=6°, MVD =92 μm. 

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

NACA 64A008 

Finite Swept Tail

(Inboard)

α = 6 deg., MVD = 92 μm

Analysis

(LEWICE3D, Inboard)

Analysis

(LEWICE3D, Outboard)

Test Data

(Laser System)

Exp. Impingement Limit:

Upper Surface = -20 mm

Lower Surface = +400 mm

βmax= 0.70 at S = +3 mm

Area of β curve per unit span = 41.69 mm2

Total Impingement Efficiency = 0.359

NASA/TM—2002-211700 245
Fig. 104a Impingement efficiency distribution for 25%-scale Business Jet Empennage; 

Inboard, V∞ = 176 mph, α= -1°, δ=0°, MVD =11 μm (Continued). 

-120 -90 -60 -30 0 30 60 90 120

 <-- Suction Surface | Pressure Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

25% Scale Business Jet Empennage

(Inboard)

α = -1 deg., δ = 0 deg. MVD = 11 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Suction Surface = -20 mm

Pressure Surface = +20 mm

βmax= 0.60 at S = 0 mm

Area of β curve per unit span = 7.47 mm 2

Total Impingement Efficiency = 0.257

NASA/TM—2002-211700 246
Fig. 104b Impingement efficiency distribution for 25%-scale Business Jet Empennage; 

Inboard, V∞ = 176 mph, α= -1°, δ=0°, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Suction Surface | Pressure Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

25% Scale Business Jet Empennage

(Inboard)

α = -1 deg., δ = 0 deg. MVD = 21 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Suction Surface = -40 mm

Pressure Surface = +50 mm

βmax= 0.70 at S = 0 mm

Area of β curve per unit span = 11.74 mm2

Total Impingement Efficiency = 0.404

NASA/TM—2002-211700 247
Fig. 104c Impingement efficiency distribution for 25%-scale Business Jet Empennage; 

Inboard, V∞ = 176 mph, α= -1°, δ=0°, MVD =94 μm (Continued).

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Suction Surface | Pressure Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

25% Scale

Business Jet

Empennage

(Inboard)

α = -1 deg., δ = 0 deg. 

MVD = 94 μm

Analysis

(LEWICE3D)

Test Data

(Laser System)

Exp. Impingement Limits:

Suction Surface = -40 mm

Pressure Surface = +50 mm

βmax= 0.80 at S = +1 mm

Area of β curve per unit span = 13.33 mm2

Total Impingement Efficiency = 0.459

NASA/TM—2002-211700 248
Fig. 104d Impingement efficiency distribution for 25%-scale Business Jet Empennage; 

Inboard, V∞ = 176 mph, α= -6°, δ=0°, MVD =11 μm (Continued).

-90 -60 -30 0 30 60 90 120 150

<-- Suction Surface | Pressure Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

25 %Scale Business Jet Empennage

(Inboard)

α = -6 deg., δ = 0 deg., MVD = 11 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Suction Surface = -10 mm

PressureSurface = +80 mm

βmax= 0.59 at S = +3 mm

Area of β curve per unit span = 10.13 mm2

Total Impingement Efficiency = 0.224

NASA/TM—2002-211700 249
Fig. 104e Impingement efficiency distribution for 25%-scale Business Jet Empennage; 

Inboard, V∞ = 176 mph, α= -6°, δ=0°, MVD =21 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180

<-- Suction Surface | Pressure Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

25% Scale Business Jet Empennage

(Inboard)

α = -6 deg., δ = 0 deg., MVD = 21 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Suction Surface = -15 mm

Pressure Surface = +150 mm

βmax= 0.68 at S = +3 mm

Area of β curve per unit span = 15.42 mm2

Total Impingement Efficiency = 0.341

NASA/TM—2002-211700 250
Fig. 104f Impingement efficiency distribution for 25%-scale Business Jet 

Empennage; Inboard, V∞ = 176 mph, α= -6°, δ=0°, MVD =94 μm (Continued). 

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

<-- Suction Surface | Pressure Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

25% Scale Business Jet

Empennage

(Inboard)

α = - 6 deg., δ = 0 deg., MVD = 94 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Suction Surface = -20 mm

Pressure Surface = +150 mm

βmax= 0.77 at S = +3 mm

Area of β curve per unit span = 15.94 mm 2

Total Impingement Efficiency = 0.352

NASA/TM—2002-211700 251
Fig. 104g Impingement efficiency distribution for 25%-scale Business Jet Empennage; 

Outboard, V∞ = 176 mph, α= -1°, δ=0°, MVD =11 μm (Continued).

-120 -90 -60 -30 0 30 60 90 120

 <-- Suction Surface | Pressure Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

25% Scale Business Jet Empennage

(Outboard)

α = -1 deg., δ = 0 deg. MVD = 11 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Suction Surface = -20 mm

Pressure Surface = +25 mm

βmax= 0.62 at S = 0 mm

Area of β curve per unit span = 6.79 mm2

Total Impingement Efficiency = 0.292

NASA/TM—2002-211700 252
Fig. 104h Impingement efficiency distribution for 25%-scale Business Jet Empennage; 

Outboard, V∞ = 176 mph, α= -1°, δ=0°, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- Suction Surface | Pressure Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

25% Scale Business Jet Empennage

(Outboard)

α = -1 deg., δ = 0 deg., MVD = 21 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Suction Surface = -35 mm

Pressure Surface = +40 mm

βmax= 0.73 at S = 0 mm

Area of β curve per unit span = 11.87 mm2

Total Impingement Efficiency = 0.511

NASA/TM—2002-211700 253
Fig. 104i Impingement efficiency distribution for 25%-scale Business Jet 

Empennage; Outboard, V∞ = 176 mph, α= -1°, δ=0°, MVD =94 μm (Continued).

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Suction Surface | Pressure Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

25% Scale

Business Jet

Empennage

(Outboard)

α = -1 deg., δ = 0 deg. 

MVD = 94 μm

Analysis

(LEWICE3D)

Test Data

(Laser System)

Exp. Impingement Limits:

Suction Surface = -40 mm

Pressure Surface = +45 mm

βmax= 0.81 at S = +1 mm

Area of β curve per unit span = 10.99 mm 2

Total Impingement Efficiency = 0.473

NASA/TM—2002-211700 254
Fig. 104j Impingement efficiency distribution for 25%-scale Business Jet 

Empennage; Outboard, V∞ = 176 mph, α=-6°, δ=0°, MVD =11 μm (Continued).

-90 -60 -30 0 30 60 90 120 150

<-- Suction Surface | Pressure Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

25% Scale Business Jet Empennage

(Outboard)

α = -6 deg., δ = 0 deg., MVD = 11 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Suction Surface = -10 mm

PressureSurface = +70 mm

βmax= 0.62 at S = +2 mm

Area of β curve per unit span = 10.27 mm2

Total Impingement Efficiency = 0.283

NASA/TM—2002-211700 255
Fig. 104k Impingement efficiency distribution for 25%-scale Business Jet Empennage; 

Outboard, V∞ = 176 mph, α=-6°, δ=0°, MVD =21 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180

<-- Suction Surface | Pressure Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

25% Scale Business 

Jet Empennage

(Outboard)

α = -6 deg., δ = 0 deg., MVD = 21 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Suction Surface = -15 mm

Pressure Surface = +150 mm

βmax= 0.71 at S = +3 mm

Area of β curve per unit span = 17.48 mm2

Total Impingement Efficiency = 0.482

NASA/TM—2002-211700 256
Fig. 104l Impingement efficiency distribution for 25%-scale Business Jet 

Empennage; Outboard, V∞ = 176 mph, α=-6°, δ=0°, MVD =94 μm.

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

<-- Suction Surface | Pressure Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

25% Scale Business Jet

Empennage 

(Outboard)

α = -6 deg., δ = 0 deg., MVD = 94 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Suction Surface = -20 mm

Pressure Surface = +150 mm

βmax= 0.77 at S = +2 mm

Area of β curve per unit span = 13.19 mm 2

Total Impingement Efficiency = 0.364

NASA/TM—2002-211700 257
Fig. 105a Impingement efficiency distribution for full-scale Business Jet horizontal tail; 

Inboard, V∞ = 176 mph, α=1°, δ=0°, MVD =11 μm (Continued).

-120 -90 -60 -30 0 30 60 90 120

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Full Scale Business 

Jet Horizontal Tail

(Inboard)

α = 1 deg., δ = 0 deg. MVD = 11 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -35 mm

Lower Surface = +30 mm

βmax= 0.44 at S = -1 mm

Area of β curve per unit span = 7.71 mm2

Total Impingement Efficiency = 0.108

NASA/TM—2002-211700 258
Fig. 105b Impingement efficiency distribution for full-scale Business Jet horizontal tail; 

Inboard, V∞ = 176 mph, α=1°, δ=0°, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Full Scale Business 

Jet Horizontal Tail

(Inboard)

α = 1 deg., δ = 0 deg. MVD = 21 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -70 mm

Lower Surface = +45 mm

βmax= 0.58 at S = 0 mm

Area of β curve per unit span = 16.30 mm 2

Total Impingement Efficiency = 0.229

NASA/TM—2002-211700 259
Fig. 105c Impingement efficiency distribution for full-scale Business Jet horizontal tail; 

Inboard, V∞ = 176 mph, α=1°, δ=0°, MVD =94 μm (Continued).

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Full Scale

Business Jet

Horizontal Tail

(Inboard)

α = 1 deg., δ = 0 deg. 

MVD = 94 μm

Analysis

(LEWICE3D)

Test Data

(Laser System)

Exp. Impingement Limits:

Upper Surface = -120 mm

Lower Surface = +110 mm

βmax= 0.72 at S = -1 mm

Area of β curve per unit span = 21.21 mm 2

Total Impingement Efficiency = 0.298

NASA/TM—2002-211700 260
Fig. 105d Impingement efficiency distribution for full-scale Business Jet horizontal tail; 

Inboard, V∞ = 176 mph, α=6°, δ=0°, MVD =21 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180

<-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Full Scale Business 

Jet Horizontal Tail

(Inboard)

α = 6 deg., δ = 0 deg., MVD = 21 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -35 mm

Lower Surface = +305 mm

βmax= 0.57 at S = +5 mm

Area of β curve per unit span = 18.57 mm 2

Total Impingement Efficiency = 0.156

NASA/TM—2002-211700 261
Fig. 105e Impingement efficiency distribution for full-scale Business Jet horizontal tail; 

Outboard, V∞ = 176 mph, α=1°, δ=0°, MVD =11 μm (Continued).

-120 -90 -60 -30 0 30 60 90 120

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Full-Scale Business Jet 

Horizontal Tail

(Outboard)

α = 1 deg., δ = 0 deg. MVD = 11 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -35 mm

Lower Surface = +30 mm

βmax= 0.46 at S = 0 mm

Area of β curve per unit span = 8.66 mm2

Total Impingement Efficiency = 0.132

NASA/TM—2002-211700 262
Fig. 105f Impingement efficiency distribution for full-scale Business Jet horizontal tail; 

Outboard, V∞ = 176 mph, α=1°, δ=0°, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Full-Scale Business Jet 

Horizontal Tail

(Outboard)

α = 1 deg., δ = 0 deg. MVD = 21 μm

Analysis (LEWICE3D, Outboard)

Test Data (Laser System, Outboard)

Exp. Impingement Limits:

Upper Surface = -70 mm

Lower Surface = +45 mm

βmax= 0.61 at S = -1 mm

Area of β curve per unit span = 15.87 mm2

Total Impingement Efficiency = 0.242

NASA/TM—2002-211700 263
Fig. 105g Impingement efficiency distribution for full-scale Business Jet horizontal tail; 

Outboard, V∞ = 176 mph, α=1°, δ=0°, MVD =94 μm (Continued).

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Full-Scale

Business Jet

Horizontal Tail

(Outboard)

α = 1 deg., δ = 0 deg. 

MVD = 94 μm

Analysis

(LEWICE3D)

Test Data

(Laser System)

Exp. Impingement Limits:

Upper Surface = -120 mm

Lower Surface = +110 mm

βmax= 0.75 at S = 0 mm

Area of β curve per unit span = 23.66 mm 2

Total Impingement Efficiency = 0.360

NASA/TM—2002-211700 264
Fig. 105h Impingement efficiency distribution for full-scale Business Jet horizontal tail; 

Outboard, V∞ = 176 mph, α=6°, δ=0°, MVD =21 μm.

-90 -60 -30 0 30 60 90 120 150 180

<-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Full-Scale Business Jet 

Horizontal Tail Section

(Outboard)

α = 6 deg., δ = 0 deg., MVD = 21 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -35 mm

Lower Surface = +305 mm

βmax= 0.61 at S = +3 mm

Area of β curve per unit span = 22.78 mm2

Total Impingement Efficiency = 0.186

NASA/TM—2002-211700 265
Fig. 106a Impingement efficiency distribution for three-element high lift system; 

 slat element, LE down, V∞ = 176 mph, α=0°, δslat=30°, MVD =11.5 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element High Lift System

Slat Element

α = 0 deg., δslat = 30 deg., L. E. down

MVD = 11.5 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -71 mm

Lower Surface = +15 mm

βmax= 0.35 at S = -5 mm

Area of β curve per unit span = 9.29 mm2

Total Impingement Efficiency = 0.040

NASA/TM—2002-211700 266
Fig. 106b Impingement efficiency distribution for three-element high lift system; 

 slat element, LE down, V∞ = 176 mph, α=0°, δslat=30°, MVD =21 μm (Continued).

-180 -150 -120 -90 -60 -30 0 30 60 90 120

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element High Lift System

Slat Element

α = 0 deg., δslat = 30 deg., L. E. down

 MVD = 21 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -142 ++ mm

Lower Surface = +20 mm

++ end of blotter strip

βmax= 0.60 at S = -7 mm

Area of β curve per unit span = 27.46 mm 2

Total Impingement Efficiency = 0.119

NASA/TM—2002-211700 267
Fig. 106c Impingement efficiency distribution for three-element high lift system; 

 slat element, LE down, V∞ = 176 mph, α=0°, δslat=30°, MVD =92 μm (Continued).

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element 

High Lift System

Slat Element

α = 0 deg.

δslat = 30 deg., L. E. down

MVD = 92 μm

Analysis

(LEWICE3D)

Test Data

(Laser System)

Exp. Impingement Limit:

Upper Surface = -142 ++ mm

Lower Surface = +25 mm

++ end of blotter strip

βmax= 0.84 at S = -7 mm

Area of β curve per unit span = 60.23 mm2

Total Impingement Efficiency = 0.260

NASA/TM—2002-211700 268
Fig. 106d Impingement efficiency distribution for three-element high lift system; 

 main element, V∞ = 176 mph, α=0°, MVD =11.5 μm (Continued).

-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270 300

<-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-Element

High Lift System

Main Element

α = 0 deg., MVD = 11.5 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = 0 mm

Lower Surface = +110 mm

βmax= 0.05 at S = +35 mm

Area of β curve per unit span = 1.46 mm2

Total Impingement Efficiency = 0.006

NASA/TM—2002-211700 269
Fig. 106e Impingement efficiency distribution for three-element high lift system; 

 main element, V∞ = 176 mph, α=0°, MVD =21 μm (Continued).

-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270 300

<-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-Element

High Lift System

Main Element

α = 0 deg., MVD = 21 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = 0 mm

Lower Surface = +275 mm

βmax= 0.04 at S = +21 mm

Area of β curve per unit span = 4.76 mm 2

Total Impingement Efficiency = 0.021

NASA/TM—2002-211700 270
Fig. 106f Impingement efficiency distribution for three-element high lift system; 

 main element, V∞ = 176 mph, α=0°, MVD =92 μm (Continued).

-60 -30 0 30 60 90 120 150 180 210 240 270 300

<-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-Element 

High Lift System

Main Element

α = 0 deg., MVD = 92 μm

Analysis (LEWICE)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = NA

Lower Surface = +160-370 mm

βmax= 0.04 at S = +204 mm

Area of β curve per unit span = 1.18 mm2

Total Impingement Efficiency = 0.005

NASA/TM—2002-211700 271
Fig. 106g Impingement efficiency distribution for three-element high lift system; flap 

element, TE down, V∞ = 176 mph, α=0°, δflap=30°, MVD =11.5 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element High Lift System

Flap Element

α = 0 deg., δflap = 30 deg., T. E. down

MVD = 11.5 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -4 mm

Lower Surface = +286 ++ mm

βmax= 0.29 at S = +14 mm

Area of β curve per unit span = 11.81 mm 2

Total Impingement Efficiency = 0.051

++ end of blotter strip

NASA/TM—2002-211700 272
Fig. 106h Impingement efficiency distribution for three-element high lift system; 

 flap element, TE down, V∞ = 176 mph, α=0°, δflap=30°, MVD =21 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element High Lift System

Flap Element

α = 0 deg., δflap = 30 deg., T. E. down

MVD = 21 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -4 mm

Lower Surface = +286 ++ mm

++ end of blotter strip

βmax= 0.51 at S = +24 mm

Area of β curve per unit span = 47.96 mm2

Total Impingement Efficiency = 0.207

NASA/TM—2002-211700 273
Fig. 106i Impingement efficiency distribution for three-element high lift system; 

 flap element, TE down, V∞ = 176 mph, α=0°, δflap=30°, MVD =92 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element 

High Lift System

Flap Element

α = 0 deg., δflap = 30 deg., T. E. down

MVD = 92 μm

Analysis (LEWICE3D)

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -4 mm

Lower Surface = +286 ++ mm

++ end of blotter strip

βmax= 0.74 at S = +24 mm

Area of β curve per unit span = 96.72 mm2

Total Impingement Efficiency = 0.418

NASA/TM—2002-211700 274
Fig. 106j Impingement efficiency distribution for three-element high lift system; 

 cove region, TE down, V∞ = 176 mph, α=0°, δflap=30°, MVD =11.5 μm (Continued).

0 30 60 90 120 150 180

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element

High Lift System

Cove Region

α = 0 deg., δflap = 30 deg., 

T. E. down

MVD = 11.5 μm

Test Data (Laser System)

Highlight for cove region

Cove region

NASA/TM—2002-211700 275
Fig. 106k Impingement efficiency distribution for three-element high lift system; 

 cove region, TE down, V∞ = 176 mph, α=0°, δflap=30°, MVD =21 μm (Continued).

0 30 60 90 120 150 180

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element

High Lift System

Cove

α = 0 deg., δflap = 30 deg., 

T. E. down

MVD = 21 μm

Test Data (Laser System)

Highlight for cove region

Cove region

NASA/TM—2002-211700 276
Fig. 106l Impingement efficiency distribution for three-element high lift system; 

 slat element, LE down, V∞ = 176 mph, α=4°, δslat=30°, MVD =11.5 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element High Lift System

Slat Element

α = 4 deg., δslat = 30 deg., L. E. down

MVD = 11.5 μm

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -35 mm

Lower Surface = +30 mm

Note: analysis data not available

βmax= 0.35 at S = +2 mm

Area of β curve per unit span = 7.70 mm2

Total Impingement Efficiency = 0.026

NASA/TM—2002-211700 277
Fig. 106m Impingement efficiency distribution for three-element high lift system; 

 slat element, LE down, V∞ = 176 mph, α=4°, δslat=30°, MVD =21 μm (Continued).

-180 -150 -120 -90 -60 -30 0 30 60 90 120

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element High Lift System

Slat Element

α = 4 deg., δslat = 30 deg., L. E. down

MVD = 21 μm

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -142 ++ mm

Lower Surface = +37 mm

Note: analysis data

 not available

++ end of blotter strip

βmax= 0.64 at S = +2 mm

Area of β curve per unit span = 22.12 mm 2

Total Impingement Efficiency = 0.076

NASA/TM—2002-211700 278
Fig. 106n Impingement efficiency distribution for three-element high lift system; 

 slat element, LE down, V∞ = 176 mph, α=4°, δslat=30°, MVD =92 μm (Continued).

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150

 <-- U pper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element 

High Lift System

Slat Element

α = 4 deg.

δslat = 30 deg., L. E. down

MVD = 92 μm

Test Data

(Laser System)

Exp. Impingement Limits:

Upper Surface = -142 ++ mm

Lower Surface = +40 mm

Note: analysis data 

 not available

++ end of blotter strip

βmax= 0.82 at S = +1 mm

Area of β curve per unit span = 43.62 mm2

Total Impingement Efficiency = 0.149

NASA/TM—2002-211700 279
Fig. 106o Impingement efficiency distribution for three-element high lift system; 

 main element, V∞ = 176 mph, α=4°, MVD =11.5 μm (Continued).

-90 -60 -30 0 30 60 90 120 150

 <-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element High Lift System

Main Element

α = 4 deg., MVD = 11.5 μm

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = NA mm

Lower Surface = +130 mm

Note: analysis data not available

βmax= 0.40 at S = +20 mm

Area of β curve per unit span = 14.94 mm2

Total Impingement Efficiency = 0.051

NASA/TM—2002-211700 280
Fig. 106p Impingement efficiency distribution for three-element high lift system; 

 main element, V∞ = 176 mph, α=4°, MVD =21 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180 210 240 270

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element High Lift System

Main Element

α = 4 deg., MVD = 21 μm

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = 0 mm

Lower Surface = +300 mm

Note: analysis data not available

βmax= 0.38 at S = +24 mm

Area of β curve per unit span = 33.41 mm 2

Total Impingement Efficiency = 0.114

NASA/TM—2002-211700 281
Fig. 106q Impingement efficiency distribution for three-element high lift system; 

 main element, V∞ = 176 mph, α=4°, MVD =92 μm (Continued).

-100 -50 0 50 100 150 200 250 300 350 400 450

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element High Lift System

Main Element

α = 4 deg., MVD = 92 μm

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = NA mm

Lower Surface = +420 mm

Note: analysis data not available

βmax= 0.30 at S = +85 mm

Area of β curve per unit span = 42.47 mm2

Total Impingement Efficiency = 0.145

NASA/TM—2002-211700 282
Fig. 106r Impingement efficiency distribution for three-element high lift system; 

 flap element, TE down, V∞ = 176 mph, α=4°, δflap=30°, MVD =11.5 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element High Lift System

Flap Element

α = 4 deg., δflap = 30 deg., T. E. down

MVD = 11.5 μm

Test Data (Laser System)

Exp. Impingement Limits:

Upper Surface = -4 mm

Lower Surface = +286 ++ mm

++ end of blotter strip

βmax= 0.23 at S = +15 mm

Area of β curve per unit span = 9.42 mm2

Total Impingement Efficiency = 0.032

Note: analysis data not available

NASA/TM—2002-211700 283
Fig. 106s Impingement efficiency distribution for three-element high lift system; 

 flap element, TE down, V∞ = 176 mph, α=4°, δflap=30°, MVD =21 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element High Lift System

Flap Element

α = 4 deg., δflap = 30 deg., T. E. down

MVD = 21 μm

Test Data (Laser System)

++ end of blotter strip

Exp. Impingement Limits:

Upper Surface = -4 mm

Lower Surface = +286 ++ mm

βmax= 0.53 at S = +16 mm

Area of β curve per unit span = 51.37 mm2

Total Impingement Efficiency = 0.176

Note: analysis data not available

NASA/TM—2002-211700 284
Fig. 106t Impingement efficiency distribution for three-element high lift system; flap 

element, TE down, V∞ = 176 mph, α=4°, δflap=30°, MVD =92 μm (Continued).

-90 -60 -30 0 30 60 90 120 150 180 210 240 270

 <-- U pper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element 

High Lift System

Flap Element

α = 4 deg.

δflap = 30 deg., T. E. down

 MVD = 92 μm

Test Data (Laser System)

++ end of blotter strip

Exp. Impingement Limits:

Upper Surface = -4 mm

Lower Surface = +286 ++ mm

βmax= 0.78 at S = +22 mm

Area of β curve per unit span = 110.9 mm 2

Total Impingement Efficiency = 0.379

Note: analysis data not available

NASA/TM—2002-211700 285
Fig. 106u Impingement efficiency distribution for three-element high lift system; 

 cove region, TE down, V∞ = 176 mph, α=4°, δflap=30°, MVD =11.5 μm (Continued).

0 30 60 90 120 150 180

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element

High Lift System

Cove

α = 4 deg., δflap = 30 deg., 

T. E. down

MVD = 11.5 μm

Test Data (Laser System)

Highlight for cove region

Cove region

NASA/TM—2002-211700 286
Fig. 106v Impingement efficiency distribution for three-element high lift system; 

 cove region, TE down, V∞ = 176 mph, α=4°, δflap=30°, MVD =21 μm (Continued).

0 30 60 90 120 150 180

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

Three-element

High Lift System

Cove

α = 4 deg., δflap = 30 deg., 

T. E. down

MVD = 21 μm

Test Data (Laser System)

Highlight for cove region

Cove region

NASA/TM—2002-211700 287
Fig. 107a Impingement efficiency distribution for S-duct engine inlet; 

locations A and B, V∞ = 170 mph, α=0°, CAR=0.65, MVD =11 μm (Continued). 

-200 -100 0 100 200 300 400 500 600 700

<-- Outer Surface | Inner Surface --> 

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

S-Duct Engine Inlet

Locations A and B

MVD = 11 μm, V∞ = 170 mph

Capture Area Ratio = 0.65

Mass Flow Rate = 23 lbm/sec

Analysis (LEWICE3D)

1999 Test Data (Laser System)

(location A)

1999 Test Data (Laser System)

(location B)

NASA/TM—2002-211700 288
Fig. 107b Impingement efficiency distribution for S-duct engine inlet; 

locations A and B, V∞ = 170 mph, α=0°, CAR=0.65, MVD =21 μm (Continued).

-200 -100 0 100 200 300 400 500 600 700

<-- Outer Surface | Inner Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

S-Duct Engine Inlet

Locations A and B

MVD = 21 μm, V∞ = 170 mph

Capture Area Ratio = 0.65

Mass Flow Rate = 23 lbm/sec

Analysis (LEWICE3D)

1999 Test Data (Laser System)

(location A)

1999 Test Data (Laser System)

(location B)

NASA/TM—2002-211700 289
Fig. 107c Impingement efficiency distribution for S-duct engine inlet; 

locations A and B, V∞ = 170 mph, α=0°, CAR=0.65, MVD =94 μm (Continued).

-200 -100 0 100 200 300 400 500 600 700

<-- Outer Surface | Inner Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

S-Duct Engine Inlet

Locations A and B

MVD = 94 μm, V∞ = 170 mph

C apture A rea R atio = 0.65

Mass Flow R ate = 23 lbm/sec

Analysis (LEWICE3D)

1999 Test Data (Laser System)

(location A)

1999 Test Data (Laser System)

(location B)

NASA/TM—2002-211700 290
Fig. 107d Impingement efficiency distribution for S-duct engine inlet; 

location C, V∞ = 170 mph, α=0°, CAR=0.65, MVD =11 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270 300

 <-- Inlet Flange | Scavenge Duct -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

S-Duct Engine Inlet

Location C

MVD = 11 μm, V∞ = 170 mph

Capture Area Ratio = 0.65

Mass Flow Rate = 23 lbm/sec

Analysis (LEWICE3D)

1999 Test Data (Laser System)

NASA/TM—2002-211700 291
Fig. 107e Impingement efficiency distribution for S-duct engine inlet; 

location C, V∞ = 170 mph, α=0°, CAR=0.65, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270 300

 <-- Inlet Flange | Scavenge Duct -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

S-Duct Engine Inlet

Location C

MVD = 21 μm, V∞ = 170 mph

Capture Area Ratio = 0.65

Mass Flow Rate = 23 lbm/sec

Analysis (LEWICE3D)

1999 Test Data (Laser System)

NASA/TM—2002-211700 292
Fig. 107f Impingement efficiency distribution for S-duct engine inlet; 

location C, V∞ = 170 mph, α=0°, CAR=0.65, MVD =94 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270 300

 <-- Inlet Flange | Scavenge -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

S-Duct Engine Inlet

Location C

MVD = 94 μm, V∞ = 170 mph

Capture Area Ratio = 0.65

Mass Flow Rate = 23 lbm/sec

Analysis (LEWICE3D)

1999 Test Data (Laser System)

NASA/TM—2002-211700 293
Fig. 107g Impingement efficiency distribution for S-duct engine inlet; 

location D, V∞ = 170 mph, α=0°, CAR=0.65, MVD =11 μm (Continued).

-270 -240 -210 -180 -150 -120 -90 -60 -30 0 30

A ir Flow →

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

S-Duct Engine Inlet

MVD = 11 μm, V∞ = 170 mph

Capture Area Ratio = 0.65

Mass Flow Rate = 23 lbm/sec

Analysis (LEWICE3D)

1999 Test data (Laser System)

NASA/TM—2002-211700 294
Fig. 107h Impingement efficiency distribution for S-duct engine inlet; 

location D, V∞ = 170 mph, α=0°, CAR=0.65, MVD =21 μm (Continued).

-270 -240 -210 -180 -150 -120 -90 -60 -30 0 30

A ir Flow →

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

S-Duct Engine Inlet

MVD = 21 μm, V∞ = 170 mph

Capture Area Ratio = 0.65

Mass Flow Rate = 23 lbm/sec

Analysis (LEWICE3D)

1999 Test data (Laser System)

NASA/TM—2002-211700 295
Fig. 107i Impingement efficiency distribution for S-duct engine inlet; 

location D, V∞ = 170 mph, α=0°, CAR=0.65, MVD =94 μm (Continued).

-270 -240 -210 -180 -150 -120 -90 -60 -30 0 30

A ir Flow →

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

S-Duct Engine Inlet

MVD = 94 μm, V∞ = 170 mph

Capture Area Ratio = 0.65

Mass Flow Rate = 23 lbm/sec

Analysis (LEWICE3D)

1999 Test data (Laser System)

NASA/TM—2002-211700 296
Fig. 107j Impingement efficiency distribution for S-duct engine inlet; 

locations A and B, V∞ = 130 mph, α=0°, CAR=0.84, MVD =21 μm (Continued).

-200 -100 0 100 200 300 400 500 600 700

<-- Outer Surface | Inner Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

S-Duct Engine Inlet

Locations A and B

MVD = 21 μm, V∞ = 130 mph

Capture Area Ratio = 0.84

Mass Flow Rate = 23 lbm/sec

1999 Test Data (Laser System)

(location A)

1999 Test Data (Laser System)

(location B)

NASA/TM—2002-211700 297
Fig. 107k Impingement efficiency distribution for S-duct engine inlet; 

locations A and B, V∞ = 130 mph, α=0°, CAR=0.84, MVD =94 μm (Continued).

-200 -100 0 100 200 300 400 500 600 700

<-- Outer Surface | Inner Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

S-Duct Engine Inlet

Locations A and B

MVD = 94 μm, V∞ = 130 mph

Capture Area Ratio = 0.84

Mass Flow Rate = 23 lbm/sec

1999 Test Data (Laser System)

(location A)

1999 Test Data (Laser System)

(location B)

NASA/TM—2002-211700 298
Fig. 107l Impingement efficiency distribution for S-duct engine inlet; 

location C, V∞ = 130 mph, α=0°, CAR=0.84, MVD =21 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270 300

 <-- Inlet Flange | Scavenge D uct -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

S-Duct Engine Inlet

Location C

MVD = 21 μm, V∞ = 130 mph

Capture Area Ratio = 0.84

Mass Flow Rate = 23 lbm/sec

1999 Test Data (Laser System)

NASA/TM—2002-211700 299
Fig. 107m Impingement efficiency distribution for S-duct engine inlet; 

location C, V∞ = 130 mph, α=0°, CAR=0.84, MVD =94 μm (Continued).

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270 300

 <-- Inlet Flange | Scavenge -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

S-Duct Engine Inlet

Location C

MVD = 94 μm, V∞ = 130 mph

Capture Area Ratio = 0.84

Mass Flow Rate = 23 lbm/sec

1999 Test Data (Laser System)

NASA/TM—2002-211700 300
Fig. 107n Impingement efficiency distribution for S-duct engine inlet; 

location D, V∞ = 130 mph, α=0°, CAR=0.84, MVD =21 μm (Continued).

-270 -240 -210 -180 -150 -120 -90 -60 -30 0 30

Air Flow →

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

S-Duct Engine Inlet

Location D

MVD = 21 μm, V∞ = 130 mph

Capture Area Ratio = 0.84

Mass Flow Rate = 23 lbm/sec

1999 Test data (Laser System)

NASA/TM—2002-211700 301
Fig. 107o Impingement efficiency distribution for S-duct engine inlet; 

location D, V∞ = 130 mph, α=0°, CAR=0.84, MVD =94 μm (Continued).

-270 -240 -210 -180 -150 -120 -90 -60 -30 0 30

Air Flow →

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (

β)

S-Duct Engine Inlet

Location D

MVD = 94 μm, V∞ = 130 mph

Capture Area Ratio = 0.84

Mass Flow Rate = 23 lbm/sec

1999 Test data (Laser System)

NASA/TM—2002-211700 302
a. AOA = 0 deg. 

b. AOA = 8 deg. 

Fig. 108 Experimental impingement limits for MS-317 airfoil - 1997 IRT tests 

(Continued).

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11.5 μm

MVD=21 μm

MVD=92 μm

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11.5 μm

MVD=21 μm

MVD=92 μm

NASA/TM—2002-211700 303
c. AOA = 0 deg.

Fig. 108 Experimental impingement limits for MS-317 airfoil - 1999 IRT tests.

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11 μm

MVD=21 μm

MVD=94 μm

NASA/TM—2002-211700 304
a. AOA = 1.5 deg. 

b. AOA = 6 deg. 

Fig. 109 Experimental impingement limits for GLC-305 airfoil - 1997 IRT tests.

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11.5 μm

MVD=21 μm

MVD=92 μm

End of Blotter Strip Reached

End of Blotter 

Strip Reached

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

End of Blotter Strip Reached

MVD=11.5 μm

MVD=21 μm

MVD=92 μm

NASA/TM—2002-211700 305
a. AOA = 0 deg. 

b. AOA = 8 deg. 

Fig. 110 Experimental impingement limits for NACA 652-415 airfoil - 1997 IRT tests. 

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11.5 μm

MVD=21 μm

MVD=92 μm

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11.5 μm

MVD=21 μm

MVD=92 μm

End of Blotter Strip Reached

End of Blotter Strip Reached

NASA/TM—2002-211700 306
a. AOA = 0 deg.

b. AOA = 4 deg. 

Fig. 111 Experimental impingement limits for commercial transport tail section -

1997 IRT tests.

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11.5 μ m

MVD=21 μ m

MVD=92 μ m

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11.5 μ m

MVD=21 μ m

MVD=92 μ m

End of Blotter Strip Reached

NASA/TM—2002-211700 307
a. AOA = 0 deg. 

b. AOA = 6 deg. 

Fig. 112 Experimental impingement limits for NACA 64A008 tail section - 

1997 IRT tests. 

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11.5 μm

MVD=21 μm

MVD=92 μm

End of Blotter Strip Reached

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11.5 μm

MVD=21 μm

MVD=92 μm

NASA/TM—2002-211700 308
a. AOA = 0 deg. 

b. AOA = 8 deg. 

Fig. 113 Experimental impingement limits for 36-in NLF(1)-0414 airfoil - 

1999 IRT tests.

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11 μm

MVD=21 μm

MVD=94 μm

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11 μm

MVD=21 μm

MVD=94 μm

NASA/TM—2002-211700 309
a. AOA = 0 deg., δ = 0 deg. 

b. AOA = 4 deg., δ = 0 deg. 

Fig. 114 Experimental impingement limits for 48-in NLF(1)-0414 airfoil - 

1999 IRT tests (Continued).

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11 μm

MVD=21 μm

MVD=94 μm

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11 μm

MVD=21 μm

MVD=94 μm

NASA/TM—2002-211700 310
c. AOA = 8 deg., δ = 0 deg. 

d. AOA = 0 deg., δ = 15 deg. 

Fig. 114 Experimental impingement limits for 48-in NLF(1)-0414 airfoil - 

1999 IRT tests. 

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11 μm

MVD=21 μm

MVD=94 μm

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

MVD=11 μm

MVD=21 μm

MVD=94 μm

NASA/TM—2002-211700 311
a. AOA = -1 deg., δ = 0 deg. 

b. AOA = -6 deg., δ = 0 deg. 

Fig. 115 Experimental impingement limits for 25%-scale Business Jet Empennage, 

Inboard, 1999 IRT tests (Continued). 

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness Pressure Side

Suction Side

*Note the pressure side im pingement lim it of MVD-21 and MVD-94 are on the same point

MVD=11 μ m

MVD=21 μ m

MVD=94 μ m

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

MVD=11 μ m

MVD=21 μ m

MVD=94 μ m

Location of Maximum Thickness

Pressure Side

Suction Side

NASA/TM—2002-211700 312
a. AOA = -1 deg., δ = 0 deg. 

b. AOA = -6 deg., δ = 0 deg. 

Fig. 115 Experimental impingement limits for 25%-scale Business Jet 

Empennage; Outboard, 1999 IRT tests.

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Pressure Side Location of Maximum Thickness

Suction Side

MVD=11 μ m

MVD=21 μ m

MVD=94 μ m

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

Pressure Side

Suction Side

MVD=11 μ m

MVD=21 μ m

MVD=94 μ m

NASA/TM—2002-211700 313
a. δ = 0 deg., Inboard 

b. δ = 0 deg., Outboard 

Fig. 116 Experimental impingement limits for full-scale Business Jet horizontal 

tail - 1999 IRT tests. 

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

AOA=10, MVD=11μm

AOA=10, MVD=21 μm

AOA=10, MVD=94 μm

AOA=60, MVD=21 μm

Location of Maximum Thickness

End of Blotter Strip Reached

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.25

-0.2

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0.2

0.25

Y/C

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Location of Maximum Thickness

AOA=10, MVD=11 μm

AOA=10, MVD=21μm

AOA=10, MVD=94 μm

AOA=60, MVD=21 μm

NASA/TM—2002-211700 314
a. AOA = 0 deg. 

b. AOA = 8 deg. 

Fig. 117 Experimental impingement efficiency surface distribution for MS(1)-0317 

airfoil - 1997 IRT tests (Continued).

MVD = 11.5 μm

MVD = 21 μm

MVD = 92 μm

MVD = 11.5 μm

MVD = 21 μm

MVD = 92 μm

NASA/TM—2002-211700 315
c. AOA = 0 deg. 

Fig. 117 Experimental impingement efficiency surface distribution for MS(1)-0317 

airfoil - 1999 IRT tests. 

MVD = 11 μm

MVD = 21 μm

MVD = 94 μm

NASA/TM—2002-211700 316
a. AOA = 1.5 deg. 

b. AOA = 6 deg. 

Fig. 118 Experimental impingement efficiency surface distribution for GLC-305 

airfoil - 1997 IRT tests. 

MVD = 11.5 μm

MVD = 21 μm

MVD = 92 μm

MVD = 11.5 μm

MVD = 21 μm

MVD = 92 μm

NASA/TM—2002-211700 317
a. AOA = 0 deg. 

b. AOA = 8 deg. 

Fig. 119 Experimental impingement efficiency surface distribution for NACA 652-415

airfoil -1997 IRT tests. 

MVD = 11.5 μm

MVD = 21 μm

MVD = 92 μm

MVD = 11.5 μm

MVD = 21 μm

MVD = 92 μm

NASA/TM—2002-211700 318
a. AOA = 0 deg. 

b. AOA = 4 deg. 

Fig. 120 Experimental impingement efficiency surface distribution for commercial 

transport tail section - 1997 IRT tests. 

MVD = 11.5 μm

MVD = 21 μm

MVD = 92 μm

MVD = 11.5 μm

MVD = 21 μm

MVD = 92 μm

NASA/TM—2002-211700 319
a. AOA = 0 deg. 

b. AOA = 8 deg. 

Fig. 121 Experimental impingement efficiency surface distribution for 36-in 

NLF(1)-0414 airfoil - 1999 IRT tests. 

MVD = 11 μm

MVD = 21 μm

MVD = 94 μm

MVD = 11 μm

MVD = 21 μm

MVD = 94 μm

NASA/TM—2002-211700 320
a. AOA = 0 deg., δ = 0 deg. 

b. AOA = 4 deg., δ = 0 deg. 

Fig. 122 Experimental impingement efficiency surface distribution for 48-in 

NLF(1)-0414 Airfoil -1999 IRT tests (Continued).

MVD = 11 μm

MVD = 21 μm

MVD = 94 μm

MVD = 11 μm

MVD = 21 μm

MVD = 94 μm

NASA/TM—2002-211700 321
c. AOA = 8 deg., δ = 0 deg. 

d. AOA = 0 deg., δ = 15 deg. 

Fig. 122 Experimental impingement efficiency surface distribution for 48-in 

NLF(1)-0414 Airfoil -1999 IRT tests.

MVD = 11 μm

MVD = 21 μm

MVD = 94 μm

MVD = 11 μm

MVD = 21 μm

MVD = 94 μm

NASA/TM—2002-211700 322
a. AOA = 0 deg. 

b. AOA = 6 deg. 

Fig. 123 Experimental impingement efficiency surface distribution for NACA 64A008

tail section - 1997 IRT Tests. 

MVD = 11.5 μm

MVD = 21 μm

MVD = 92 μm

MVD = 11.5 μm

MVD = 21 μm

MVD = 92 μm

NASA/TM—2002-211700 323
a. AOA = -1 deg., δ = 0 deg., Inboard 

b. AOA = -6 deg., δ = 0 deg., Inboard 

Fig. 124 Experimental impingement efficiency surface distribution for 25%-scale 

Business Jet Empennage - 1999 IRT tests (Continued).

MVD = 11 μm

MVD = 21 μm

MVD = 94 μm

MVD = 11 μm

MVD = 21 μm

MVD = 94 μm

NASA/TM—2002-211700 324
c. AOA = -1 deg., δ = 0 deg., Outboard 

d. AOA = -6 deg., δ = 0 deg., Outboard 

Fig. 124 Experimental impingement efficiency surface distribution for 25%-scale 

Business Jet Empennage - 1999 IRT tests.

MVD = 11 μm

MVD = 21 μm

MVD = 94 μm

MVD = 11 μm

MVD = 21 μm

MVD = 94 μm

NASA/TM—2002-211700 325
a. AOA = 1 deg., δ = 0 deg., Inboard 

b. AOA = 6 deg., δ = 0 deg., Inboard 

Fig. 125 Experimental impingement efficiency surface distribution for full-scale 

Business Jet horizontal tail -1999 IRT tests (Continued).

MVD = 11 μm

MVD = 21 μm

MVD = 94 μm

MVD = 21μm

NASA/TM—2002-211700 326
c. AOA = 1 deg., δ = 0 deg., Outboard 

d. AOA = 6 deg., δ = 0 deg., Outboard 

Fig. 125 Experimental impingement efficiency surface distribution for full-scale 

Business Jet horizontal tail - 1999 IRT tests.

MVD = 11 μm

MVD = 21 μm

MVD = 94 μm

MVD = 21μm

NASA/TM—2002-211700 327
 

Fig. 126 Comparison of LEWICE results 

for MVD = 92 and 60 μm with 

experimental data; MS(1)-317, α = 0°, 

MVD = 92 μm. 

Fig. 127 Comparison of LEWICE results

for MVD = 92 and 60 μm with 

experimental data; GLC 305, α = 1.5°, 

MVD = 92 μm. 

 

Fig. 128 Comparison of LEWICE results 

for MVD = 92 and 60 μm with 

experimental data; 

NACA 652-415, α = 0°, MVD = 92 μm. 

Fig. 129 Comparison of LEWICE 

results for MVD = 92 and 60 μm with 

experimental data; 

NACA 652-415, α = 8°, MVD = 92 μm. 

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

MS(1)-317 Airfoil

α = 0 deg., MVD = 92 μm

LEWICE (MVD = 94)

LEWICE (MVD = 60)

1997 Test Data (Laser)

1999 Test Data (Laser)

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

GLC 305 Airfoil

α = 1.5 deg., MVD = 92 μm

LEWICE (MVD = 92)

LEWICE (MVD = 60)

1997 Test Data (Laser)

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 <-- Upper Surface | Lower Surface -->

Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

NACA 652-415 Airfoil

α = 0 deg., MVD = 92 μm

LEW ICE (MVD = 92)

LEW ICE (MVD = 60)

1997 Test Data (Laser)

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

<-- Upper Surface | Lower Surface -->

 Surface Distance from Highlight (mm)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Local Impingement Efficiency (β)

NACA 652-415 Airfoil

α = 8 deg., MVD = 92 μm

LEWICE (MVD = 92)

LEWICE (MVD = 60)

1997 Test Data (Laser)

NASA/TM—2002-211700 328
Fig. 130 Droplet distribution near LE of NACA-0012 airfoil; c=21-in, V∞=175 mph, 

α = 0°, MVD = 104 μm. 

Fig. 131 Droplet velocity distribution near LE of NACA-0012 airfoil; c=21-in, 

V∞=175 mph, α = 0°, MVD = 104 μm. 

Fig. 132 Velocity versus droplet size near LE of NACA-0012 airfoil; c = 21-in, 

V∞ = 175 mph, α = 0°, MVD = 104 μm. 

Group of small 

droplets with negative 

velocity

NASA/TM—2002-211700 329

 

α = 0°

MVD = 11-11.5 μm MVD = 21 μm MVD = 92-94 μm 

 

α = 8°

MVD = 11-11.5 μm MVD = 21 μm MVD = 92 μm 

 

Fig. A1 Impingement data for MS(1)-0317 airfoil. 

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.2

-0.1

0.0

0.1

0.2

Y/C

Appendix A: Summary of Experimental and LEWICE 

 Impingement Data 

Highlight 

at x/c=0 

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Analysis (LEWICE)

1997 Test Data (Laser System)

1999 Test Data (Laser System)

NASA/TM—2002-211700 331
 

α = 0°

MVD = 11.5 μm MVD = 21 μm MVD = 92 μm 

 

α = 6°

MVD = 11.5 μm MVD = 21 μm MVD = 92 μm 

 

Fig. A2 Impingement data for GLC 305 airfoil. 

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.2

-0.1

0.0

0.1

0.2

Y/C

Highlight 

at x/c=0 

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Analysis (LEWICE)

Test Data (Laser System)

NASA/TM—2002-211700 332
 

α = 0°

MVD = 11.5 μm MVD = 21 μm MVD = 92 μm 

 

α = 8°

MVD = 11.5 μm MVD = 21 μm MVD = 92 μm 

 

Fig. A3 Impingement data for NACA 65(2)-415 airfoil. 

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.2

-0.1

0.0

0.1

0.2

Y/C

Highlight 

at x/c=0 

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Analysis (LEWICE)

Test Data (Laser System)

NASA/TM—2002-211700 333
 

α = 0°

MVD = 11.5 μm MVD = 21 μm MVD = 92 μm 

 

α = 4°

MVD = 11.5 μm MVD = 21 μm MVD = 92 μm 

 

Fig. A4 Impingement data for Commercial Jet Transport Tail. 

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.2

-0.1

0.0

0.1

0.2

Y/C

Highlight 

at x/c=0 

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Analysis (LEWICE)

Test Data (Laser System)

NASA/TM—2002-211700 334
 

α = 0°

MVD = 11 μm MVD = 21 μm MVD = 94 μm 

 

α = 8°

MVD = 11 μm MVD = 21 μm MVD = 94 μm 

 

Fig. A5 Impingement data for NLF-414 36” airfoil. 

Analysis (LEWICE, 36")

1999 Test Data (Laser System)

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.2

-0.1

0.0

0.1

0.2

Y/C

Highlight 

at x/c=0 

NASA/TM—2002-211700 335
 

α = 0°

δ = 0°

MVD = 11 μm MVD = 21 μm MVD = 94 μm 

 

α = 0°

δ = 15°

MVD = 11 μm MVD = 21 μm MVD = 94 μm 

 

Fig. A6a Impingement data for NLF-414 48 “ airfoil (Cont.) 

Analysis (LEWICE, 48")

1999 Test Data (Laser System)

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.2

-0.1

0.0

0.1

0.2

Y/C

Highlight 

at x/c=0 

NASA/TM—2002-211700 336
 

α = 4°

δ = 0°

MVD = 11 μm MVD = 21 μm MVD = 94 μm 

 

α = 8°

δ = 0°

MVD = 11 μm MVD = 21 μm MVD = 94 μm 

 

Fig. A6b Impingement data for NLF-414 48 “ airfoil. 

Analysis (LEWICE, 48")

1999 Test Data (Laser System)

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.2

-0.1

0.0

0.1

0.2

Y/C

Highlight 

at x/c=0 

NASA/TM—2002-211700 337
 

α = 0°

MVD = 11.5 μm MVD = 21 μm MVD = 92 μm 

 

α = 6°

MVD = 11.5 μm MVD = 21 μm MVD = 92 μm 

 

Fig. A7 Impingement data for NACA 64A008 airfoil. 

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.2

-0.1

0.0

0.1

0.2

Y/C

Highlight 

at x/c=0 

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Analysis (Lewice3D, Inboard)

Analysis (Lewice3D, Outboard)

Test Data (Laser System)

NASA/TM—2002-211700 338
 

α = -1°

MVD = 11 μm MVD = 21 μm MVD = 94 μm 

 

α = -6°

MVD = 11 μm MVD = 21 μm MVD = 94 μm 

 

Fig. A8 Impingement data for 25% scale Business Jet Empanage. 

Analysis (LEWICE3D, Inboard)

Analysis (LEWICE3D, Outboard)

1999 Test Data 

(Laser System, Inboard)

1999 Test Data 

(Laser System, Outboard)

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210-180-150-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.2

-0.1

0.0

0.1

0.2

Y/C

suction surface

pressure surface

Highlight 

at x/c=0 

NASA/TM—2002-211700 339
 

α = 1°

MVD = 11 μm MVD = 21 μm MVD = 94 μm 

 

α = 6°

MVD = 21 μm 

 

Fig. A9 Impingement data for Full Scale Business Jet Horizontal Tail. 

Analysis 

(LEWICE3D, Inboard)

Analysis 

(LEWICE3D, Outboard)

1999 Test Data 

(Laser System, Inboard)

1999 Test Data 

(Laser System, Outboard)

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150 180 210

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.2

-0.1

0.0

0.1

0.2

Y/C

Highlight 

at x/c=0 

NASA/TM—2002-211700 340
 

α = 0°

MVD = 11.5 μm MVD = 21 μm MVD = 92 μm 

 

α = 4°

MVD = 11.5 μm MVD = 21 μm MVD = 92 μm 

 

Fig. A10a Impingement data for MD 3-element (slat element). 

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-0.2 -0.1 0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2

X/C

-0.2

-0.1

0.0

0.1

0.2

Y/C

Highlight at 

x/c=-0.085 

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-210 -180 -150 -120 -90 -60 -30 0 30 60 90 120 150

 

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Analysis (LEWICE)

Test Data (Laser System)

NASA/TM—2002-211700 341
 

α = 0°

MVD = 11.5 μm MVD = 21 μm MVD = 92 μm 

 

α = 4°

MVD = 11.5 μm MVD = 21 μm MVD = 92 μm 

 

Fig. A10b Impingement data for MD 3-element (main element). 

-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270 300

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270 300

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270 300

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270 300

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-0.2 -0.1 0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2

X/C

-0.2

-0.1

0.0

0.1

0.2

Y/C

Highlight at 

x/c=0.0438 

-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270 300

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-120 -90 -60 -30 0 30 60 90 120 150 180 210 240 270 300

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Analysis (LEWICE)

Test Data (Laser System)

NASA/TM—2002-211700 342
 

α = 0°

MVD = 11.5 μm MVD = 21 μm MVD = 92 μm 

 

α = 4°

MVD = 11.5 μm MVD = 21 μm MVD = 92 μm 

 

Fig. A10c Impingement data for MD 3-element (flap element). 

-0.2 -0.1 0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2

X/C

-0.2

-0.1

0.0

0.1

0.2

Y/C

Highlight at 

x/c=0.8715 

-90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-90 -60 -30 0 30 60 90 120 150 180 210 240 270

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

Analysis (LEWICE)

Test Data (Laser System)

NASA/TM—2002-211700 343

Appendix B: Coordinates of airfoil sections 

Fig. B-1 MS(1)-0317 Airfoil 

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.1-0.2

0.2

0.1

0.0 Y/C

NASA/TM—2002-211700 345
Table B-1 Coordinates of MS(1)–0317 Airfoil 

Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

1 -0.0024 0.3147 -0.0695 0.0000 0.0022 0.2795 0.0972 1 -0.0024 

0.9848 -0.0007 0.2977 -0.0690 0.0001 0.0042 0.2959 0.0980 

0.9725 0.0002 0.2811 -0.0684 0.0004 0.0062 0.3118 0.0986 

0.9603 0.0007 0.2643 -0.0676 0.0008 0.0081 0.3251 0.0990 

0.9469 0.0007 0.2473 -0.0667 0.0013 0.0101 0.3375 0.0993 

0.9332 0.0002 0.2306 -0.0657 0.0018 0.0120 0.3527 0.0996 

0.9193 -0.0006 0.2145 -0.0645 0.0025 0.0139 0.3690 0.0997 

0.9051 -0.0017 0.1982 -0.0631 0.0032 0.0157 0.3854 0.0997 

0.8907 -0.0032 0.1814 -0.0616 0.0040 0.0176 0.4020 0.0995 

0.8760 -0.0050 0.1657 -0.0600 0.0049 0.0193 0.4183 0.0992 

0.8612 -0.0070 0.1502 -0.0582 0.0059 0.0211 0.4341 0.0988 

0.8460 -0.0093 0.1348 -0.0562 0.0068 0.0229 0.4498 0.0983 

0.8304 -0.0119 0.1199 -0.0540 0.0079 0.0246 0.4658 0.0975 

0.8145 -0.0147 0.1055 -0.0516 0.0090 0.0262 0.4818 0.0966 

0.7981 -0.0177 0.0911 -0.0489 0.0101 0.0279 0.4971 0.0956 

0.7812 -0.0210 0.0772 -0.0459 0.0113 0.0295 0.5129 0.0943 

0.7640 -0.0244 0.0640 -0.0427 0.0126 0.0311 0.5290 0.0929 

0.7443 -0.0283 0.0496 -0.0385 0.0138 0.0326 0.5446 0.0913 

0.7249 -0.0323 0.0394 -0.0350 0.0152 0.0341 0.5601 0.0896 

0.7061 -0.0361 0.0323 -0.0321 0.0165 0.0355 0.5755 0.0877 

0.6903 -0.0392 0.0273 -0.0298 0.0180 0.0370 0.5908 0.0857 

0.6732 -0.0425 0.0238 -0.0280 0.0194 0.0383 0.6063 0.0836 

0.6576 -0.0454 0.0213 -0.0267 0.0209 0.0397 0.6223 0.0812 

0.6433 -0.0479 0.0196 -0.0257 0.0224 0.0410 0.6383 0.0787 

0.6273 -0.0507 0.0179 -0.0247 0.0245 0.0428 0.6545 0.0760 

0.6112 -0.0533 0.0162 -0.0236 0.0276 0.0453 0.6713 0.0730 

0.5956 -0.0557 0.0145 -0.0225 0.0320 0.0485 0.6871 0.0701 

0.5802 -0.0578 0.0129 -0.0213 0.0384 0.0527 0.7018 0.0673 

0.5648 -0.0597 0.0113 -0.0201 0.0479 0.0579 0.7178 0.0639 

0.5488 -0.0615 0.0098 -0.0188 0.0588 0.0628 0.7353 0.0602 

0.5328 -0.0632 0.0083 -0.0175 0.0708 0.0671 0.7518 0.0565 

0.5172 -0.0646 0.0070 -0.0160 0.0835 0.0709 0.7687 0.0528 

0.5014 -0.0658 0.0056 -0.0145 0.0967 0.0743 0.7858 0.0489 

0.4851 -0.0669 0.0044 -0.0129 0.1103 0.0774 0.8025 0.0451 

0.4690 -0.0679 0.0034 -0.0112 0.1245 0.0802 0.8211 0.0407 

0.4529 -0.0687 0.0024 -0.0095 0.1391 0.0828 0.8389 0.0365 

0.4367 -0.0693 0.0016 -0.0076 0.1541 0.0852 0.8565 0.0324 

0.4202 -0.0698 0.0010 -0.0057 0.1690 0.0873 0.8758 0.0278 

0.4061 -0.0701 0.0005 -0.0038 0.1843 0.0892 0.8946 0.0233 

0.3966 -0.0702 0.0002 -0.0018 0.2001 0.0910 0.9130 0.0189 

0.3824 -0.0703 0.0000 0.0002 0.2156 0.0925 0.9312 0.0145 

0.3655 -0.0703 0.2313 0.0939 0.9486 0.0103 

0.3487 -0.0702 0.2473 0.0952 0.9658 0.0062 

0.3317 -0.0699 0.2633 0.0962 0.9827 0.0020 

NASA/TM—2002-211700 346
0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.1

-0.2

0.2

0.1

0.0 Y/C

Fig. B-2 GLC 305 Airfoil 

NASA/TM—2002-211700 347
Table B-2 Coordinates of GLC 305 Airfoil 

Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

1 -0.0003 0.4008 -0.0372 0.0030 -0.0119 0.0000 -0.0026 0.3178 0.0484 0.8092 0.0224 

0.9832 -0.0016 0.3893 -0.0372 0.0019 -0.0103 0.0003 -0.0007 0.3288 0.0487 0.8206 0.0211 

0.9676 -0.0027 0.3778 -0.0371 0.0010 -0.0085 0.0009 0.0012 0.3398 0.0490 0.8345 0.0195 

0.9491 -0.0041 0.3662 -0.0370 0.0003 -0.0066 0.0018 0.0030 0.3506 0.0493 0.8488 0.0178 

0.9304 -0.0054 0.3542 -0.0369 0.0000 -0.0046 0.0029 0.0047 0.3614 0.0494 0.8627 0.0162 

0.9106 -0.0069 0.3421 -0.0367 0.0042 0.0062 0.3726 0.0495 0.8749 0.0148 

0.8918 -0.0083 0.3299 -0.0365 0.0057 0.0075 0.3841 0.0496 0.8892 0.0132 

0.8726 -0.0097 0.3177 -0.0363 0.0074 0.0086 0.3955 0.0496 0.9061 0.0112 

0.8535 -0.0111 0.3052 -0.0361 0.0092 0.0096 0.4069 0.0495 0.9209 0.0095 

0.8370 -0.0123 0.2930 -0.0358 0.0110 0.0104 0.4187 0.0495 0.9351 0.0078 

0.8242 -0.0133 0.2809 -0.0356 0.0128 0.0112 0.4303 0.0494 0.9495 0.0062 

0.8114 -0.0142 0.2689 -0.0353 0.0147 0.0120 0.4414 0.0493 0.9621 0.0047 

0.7985 -0.0152 0.2565 -0.0350 0.0165 0.0127 0.4524 0.0491 0.9801 0.0026 

0.7857 -0.0161 0.2437 -0.0347 0.0184 0.0134 0.4637 0.0489 1 0.0003 

0.7664 -0.0175 0.2314 -0.0343 0.0211 0.0142 0.4753 0.0486 

0.7492 -0.0188 0.2197 -0.0339 0.0248 0.0154 0.4868 0.0483 

0.7325 -0.0201 0.2079 -0.0335 0.0301 0.0170 0.4979 0.0480 

0.7200 -0.0210 0.1958 -0.0331 0.0375 0.0189 0.5090 0.0476 

0.7048 -0.0221 0.1841 -0.0326 0.0480 0.0214 0.5202 0.0471 

0.6889 -0.0233 0.1728 -0.0321 0.0580 0.0235 0.5314 0.0465 

0.6729 -0.0244 0.1610 -0.0315 0.0678 0.0254 0.5428 0.0459 

0.6576 -0.0255 0.1476 -0.0308 0.0776 0.0271 0.5535 0.0453 

0.6448 -0.0265 0.1338 -0.0301 0.0876 0.0288 0.5642 0.0447 

0.6329 -0.0273 0.1214 -0.0295 0.0980 0.0304 0.5748 0.0441 

0.6214 -0.0281 0.1094 -0.0289 0.1085 0.0319 0.5859 0.0433 

0.6096 -0.0289 0.0977 -0.0282 0.1191 0.0333 0.5968 0.0426 

0.5976 -0.0297 0.0865 -0.0275 0.1298 0.0346 0.6083 0.0417 

0.5854 -0.0304 0.0758 -0.0268 0.1405 0.0359 0.6200 0.0408 

0.5733 -0.0312 0.0655 -0.0260 0.1512 0.0371 0.6319 0.0399 

0.5611 -0.0319 0.0553 -0.0251 0.1620 0.0382 0.6441 0.0389 

0.5492 -0.0326 0.0457 -0.0241 0.1726 0.0393 0.6563 0.0378 

0.5375 -0.0332 0.0366 -0.0229 0.1828 0.0402 0.6681 0.0368 

0.5256 -0.0338 0.0290 -0.0217 0.1938 0.0412 0.6795 0.0358 

0.5136 -0.0344 0.0236 -0.0206 0.2051 0.0421 0.6910 0.0348 

0.5019 -0.0349 0.0198 -0.0197 0.2164 0.0430 0.7022 0.0338 

0.4906 -0.0354 0.0171 -0.0190 0.2274 0.0438 0.7139 0.0326 

0.4793 -0.0358 0.0152 -0.0184 0.2383 0.0445 0.7261 0.0314 

0.4680 -0.0362 0.0133 -0.0178 0.2492 0.0452 0.7381 0.0302 

0.4568 -0.0365 0.0114 -0.0171 0.2605 0.0458 0.7494 0.0291 

0.4456 -0.0368 0.0095 -0.0164 0.2721 0.0464 0.7601 0.0279 

0.4345 -0.0369 0.0077 -0.0156 0.2838 0.0470 0.7710 0.0267 

0.4234 -0.0371 0.0060 -0.0146 0.2952 0.0475 0.7823 0.0255 

0.4122 -0.0372 0.0044 -0.0134 0.3064 0.0480 0.7942 0.0241 

NASA/TM—2002-211700 348
0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.1-0.2

0.20.10.0 Y/C

Fig. B-3 NACA 652-415 Airfoil 

NASA/TM—2002-211700 349
Table B-3 Coordinates of NACA 652-415 Airfoil 

Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

1 0.0000 0.8358 -0.0078 0.6080 -0.0387 0.0000 0.0003 0.0416 0.0363 0.1891 0.0767 

0.9942 0.0004 0.8311 -0.0084 0.6030 -0.0393 -0.0002 0.0013 0.0443 0.0375 0.1931 0.0774 

0.9898 0.0007 0.8264 -0.0090 0.5981 -0.0399 -0.0002 0.0023 0.0470 0.0386 0.1971 0.0781 

0.9856 0.0009 0.8215 -0.0096 0.5939 -0.0404 -0.0002 0.0033 0.0497 0.0398 0.2011 0.0787 

0.9816 0.0011 0.8164 -0.0103 0.5902 -0.0408 -0.0001 0.0043 0.0525 0.0409 0.2052 0.0794 

0.9779 0.0013 0.8112 -0.0110 0.5849 -0.0414 0.0001 0.0053 0.0554 0.0420 0.2093 0.0800 

0.9742 0.0015 0.8061 -0.0117 0.5830 -0.0417 0.0003 0.0062 0.0582 0.0431 0.2133 0.0807 

0.9708 0.0017 0.8011 -0.0123 0.5817 -0.0418 0.0006 0.0072 0.0612 0.0442 0.2174 0.0813 

0.9674 0.0018 0.7960 -0.0130 0.5805 -0.0420 0.0010 0.0081 0.0642 0.0453 0.2216 0.0819 

0.9641 0.0019 0.7906 -0.0137 0.5786 -0.0422 0.0014 0.0090 0.0672 0.0464 0.2257 0.0825 

0.9612 0.0020 0.7851 -0.0145 0.5739 -0.0427 0.0018 0.0099 0.0704 0.0474 0.2298 0.0831 

0.9582 0.0020 0.7798 -0.0152 0.5701 -0.0431 0.0023 0.0108 0.0735 0.0485 0.2339 0.0837 

0.9551 0.0021 0.7741 -0.0160 0.5661 -0.0436 0.0028 0.0117 0.0768 0.0496 0.2381 0.0843 

0.9520 0.0021 0.7685 -0.0168 0.5617 -0.0440 0.0034 0.0125 0.0800 0.0506 0.2422 0.0848 

0.9490 0.0021 0.7618 -0.0177 0.5574 -0.0445 0.0040 0.0133 0.0833 0.0517 0.2464 0.0853 

0.9460 0.0020 0.7555 -0.0186 0.5533 -0.0449 0.0047 0.0140 0.0866 0.0527 0.2504 0.0858 

0.9432 0.0019 0.7498 -0.0194 0.5492 -0.0453 0.0054 0.0147 0.0899 0.0537 0.2544 0.0863 

0.9404 0.0019 0.7438 -0.0202 0.5447 -0.0458 0.0061 0.0155 0.0933 0.0547 0.2585 0.0868 

0.9372 0.0017 0.7377 -0.0211 0.5401 -0.0462 0.0068 0.0161 0.0967 0.0557 0.2626 0.0873 

0.9340 0.0016 0.7317 -0.0219 0.5355 -0.0467 0.0075 0.0168 0.1000 0.0567 0.2667 0.0878 

0.9307 0.0014 0.7257 -0.0227 0.5310 -0.0471 0.0083 0.0175 0.1034 0.0577 0.2708 0.0882 

0.9274 0.0012 0.7196 -0.0236 0.5266 -0.0475 0.0091 0.0181 0.1069 0.0586 0.2749 0.0887 

0.9239 0.0010 0.7136 -0.0244 0.5221 -0.0479 0.0098 0.0187 0.1103 0.0596 0.2790 0.0891 

0.9204 0.0007 0.7076 -0.0253 0.5177 -0.0482 0.0106 0.0194 0.1138 0.0605 0.2832 0.0895 

0.9167 0.0005 0.7016 -0.0261 0.5133 -0.0486 0.0114 0.0200 0.1173 0.0614 0.2873 0.0899 

0.9129 0.0002 0.6955 -0.0270 0.5090 -0.0489 0.0122 0.0205 0.1209 0.0623 0.2913 0.0903 

0.9090 -0.0002 0.6895 -0.0278 0.5046 -0.0493 0.0131 0.0211 0.1244 0.0632 0.2951 0.0907 

0.9047 -0.0006 0.6841 -0.0286 0.5004 -0.0496 0.0139 0.0217 0.1280 0.0641 0.2992 0.0910 

0.9003 -0.0010 0.6796 -0.0292 0.4960 -0.0499 0.0147 0.0222 0.1316 0.0649 0.3034 0.0914 

0.8956 -0.0014 0.6742 -0.0300 0.4917 -0.0502 0.0155 0.0228 0.1353 0.0658 0.3077 0.0918 

0.8914 -0.0018 0.6695 -0.0306 0.4874 -0.0505 0.0164 0.0233 0.1389 0.0666 0.3119 0.0921 

0.8865 -0.0023 0.6651 -0.0312 0.4830 -0.0507 0.0172 0.0239 0.1426 0.0674 0.3162 0.0924 

0.8818 -0.0027 0.6614 -0.0317 0.4786 -0.0510 0.0181 0.0244 0.1463 0.0683 0.3205 0.0928 

0.8773 -0.0032 0.6574 -0.0323 0.4743 -0.0512 0.0190 0.0249 0.1500 0.0691 0.3248 0.0931 

0.8726 -0.0037 0.6529 -0.0329 0.4699 -0.0515 0.0202 0.0256 0.1539 0.0699 0.3291 0.0934 

0.8679 -0.0042 0.6490 -0.0334 0.4655 -0.0517 0.0219 0.0266 0.1577 0.0707 0.3333 0.0936 

0.8632 -0.0047 0.6438 -0.0341 0.4612 -0.0519 0.0243 0.0279 0.1615 0.0715 0.3376 0.0939 

0.8586 -0.0052 0.6390 -0.0347 0.4568 -0.0521 0.0266 0.0291 0.1654 0.0723 0.3419 0.0942 

0.8540 -0.0057 0.6341 -0.0354 0.4524 -0.0523 0.0290 0.0304 0.1693 0.0730 0.3462 0.0944 

0.8495 -0.0062 0.6289 -0.0361 0.4481 -0.0525 0.0315 0.0316 0.1732 0.0738 0.3505 0.0947 

0.8462 -0.0066 0.6237 -0.0367 0.4438 -0.0526 0.0340 0.0328 0.1772 0.0745 0.3548 0.0949 

0.8425 -0.0070 0.6183 -0.0374 0.4395 -0.0528 0.0365 0.0340 0.1811 0.0753 0.3590 0.0951 

0.8398 -0.0074 0.6132 -0.0380 0.4351 -0.0529 0.0390 0.0352 0.1851 0.0760 0.3633 0.0953 

NASA/TM—2002-211700 350
Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

0.4307 -0.0530 0.2296 -0.0483 0.0520 -0.0258 0.3676 0.0955 0.5400 0.0902 0.7255 0.0606 

0.4263 -0.0531 0.2249 -0.0479 0.0489 -0.0250 0.3718 0.0956 0.5440 0.0898 0.7295 0.0598 

0.4219 -0.0532 0.2202 -0.0476 0.0458 -0.0243 0.3761 0.0958 0.5481 0.0894 0.7335 0.0590 

0.4175 -0.0533 0.2155 -0.0473 0.0428 -0.0236 0.3803 0.0959 0.5522 0.0889 0.7389 0.0579 

0.4132 -0.0534 0.2109 -0.0469 0.0399 -0.0228 0.3845 0.0961 0.5564 0.0884 0.7427 0.0571 

0.4087 -0.0535 0.2062 -0.0465 0.0370 -0.0220 0.3886 0.0962 0.5603 0.0880 0.7452 0.0566 

0.4043 -0.0535 0.2017 -0.0462 0.0341 -0.0213 0.3928 0.0963 0.5646 0.0874 0.7489 0.0558 

0.4001 -0.0536 0.1971 -0.0458 0.0313 -0.0205 0.3969 0.0964 0.5681 0.0870 0.7536 0.0548 

0.3957 -0.0536 0.1926 -0.0454 0.0286 -0.0196 0.4009 0.0964 0.5723 0.0865 0.7583 0.0538 

0.3912 -0.0536 0.1880 -0.0450 0.0259 -0.0188 0.4050 0.0965 0.5766 0.0859 0.7630 0.0528 

0.3866 -0.0536 0.1835 -0.0446 0.0234 -0.0180 0.4090 0.0965 0.5810 0.0854 0.7678 0.0518 

0.3820 -0.0536 0.1789 -0.0441 0.0208 -0.0171 0.4130 0.0965 0.5854 0.0848 0.7721 0.0509 

0.3774 -0.0536 0.1744 -0.0437 0.0189 -0.0164 0.4170 0.0966 0.5898 0.0842 0.7770 0.0498 

0.3727 -0.0536 0.1699 -0.0433 0.0176 -0.0159 0.4210 0.0966 0.5943 0.0835 0.7820 0.0487 

0.3680 -0.0536 0.1654 -0.0428 0.0167 -0.0155 0.4251 0.0965 0.5987 0.0829 0.7870 0.0476 

0.3633 -0.0535 0.1609 -0.0423 0.0158 -0.0151 0.4291 0.0965 0.6029 0.0823 0.7920 0.0465 

0.3585 -0.0535 0.1564 -0.0419 0.0149 -0.0147 0.4331 0.0965 0.6071 0.0817 0.7970 0.0454 

0.3537 -0.0534 0.1520 -0.0414 0.0139 -0.0143 0.4371 0.0964 0.6114 0.0810 0.8021 0.0443 

0.3489 -0.0533 0.1477 -0.0409 0.0130 -0.0139 0.4411 0.0964 0.6158 0.0804 0.8071 0.0432 

0.3441 -0.0532 0.1433 -0.0404 0.0121 -0.0134 0.4451 0.0963 0.6201 0.0797 0.8121 0.0420 

0.3395 -0.0531 0.1390 -0.0399 0.0113 -0.0130 0.4491 0.0962 0.6243 0.0790 0.8171 0.0409 

0.3348 -0.0530 0.1348 -0.0394 0.0104 -0.0125 0.4531 0.0961 0.6287 0.0783 0.8221 0.0398 

0.3301 -0.0529 0.1306 -0.0389 0.0095 -0.0120 0.4570 0.0960 0.6329 0.0777 0.8272 0.0387 

0.3253 -0.0528 0.1265 -0.0383 0.0087 -0.0114 0.4609 0.0958 0.6369 0.0770 0.8322 0.0375 

0.3206 -0.0527 0.1224 -0.0378 0.0079 -0.0109 0.4649 0.0957 0.6412 0.0763 0.8377 0.0363 

0.3158 -0.0525 0.1183 -0.0373 0.0071 -0.0102 0.4689 0.0955 0.6457 0.0755 0.8434 0.0350 

0.3110 -0.0524 0.1143 -0.0367 0.0063 -0.0096 0.4729 0.0953 0.6500 0.0748 0.8486 0.0338 

0.3063 -0.0522 0.1103 -0.0362 0.0056 -0.0090 0.4769 0.0951 0.6544 0.0740 0.8547 0.0324 

0.3015 -0.0520 0.1064 -0.0356 0.0048 -0.0083 0.4809 0.0949 0.6590 0.0732 0.8600 0.0312 

0.2968 -0.0519 0.1025 -0.0350 0.0041 -0.0075 0.4849 0.0947 0.6635 0.0724 0.8655 0.0299 

0.2920 -0.0517 0.0987 -0.0344 0.0035 -0.0068 0.4888 0.0945 0.6680 0.0716 0.8715 0.0285 

0.2872 -0.0515 0.0949 -0.0338 0.0028 -0.0060 0.4928 0.0942 0.6726 0.0708 0.8787 0.0268 

0.2824 -0.0512 0.0911 -0.0332 0.0023 -0.0052 0.4967 0.0940 0.6772 0.0700 0.8845 0.0255 

0.2775 -0.0510 0.0873 -0.0326 0.0017 -0.0044 0.5006 0.0937 0.6818 0.0691 0.8899 0.0243 

0.2727 -0.0508 0.0835 -0.0319 0.0012 -0.0035 0.5045 0.0934 0.6865 0.0682 0.8952 0.0230 

0.2678 -0.0505 0.0797 -0.0312 0.0008 -0.0026 0.5084 0.0931 0.6909 0.0674 0.9003 0.0219 

0.2630 -0.0503 0.0759 -0.0306 0.0004 -0.0017 0.5122 0.0928 0.6955 0.0665 0.9055 0.0207 

0.2582 -0.0500 0.0722 -0.0299 0.0002 -0.0007 0.5161 0.0925 0.7002 0.0656 0.9108 0.0195 

0.2534 -0.0498 0.0686 -0.0292 0.0000 0.0003 0.5201 0.0921 0.7048 0.0647 0.9164 0.0182 

0.2486 -0.0495 0.0651 -0.0285 0.5240 0.0918 0.7089 0.0639 0.9218 0.0170 

0.2439 -0.0492 0.0618 -0.0279 0.5280 0.0914 0.7132 0.0631 0.9270 0.0158 

0.2391 -0.0489 0.0584 -0.0272 0.5320 0.0910 0.7172 0.0623 0.9321 0.0146 

0.2344 -0.0486 0.0552 -0.0265 0.5361 0.0906 0.7217 0.0614 0.9370 0.0135 

NASA/TM—2002-211700 351
Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

 0.9421 0.0124 

 0.9472 0.0113 

 0.9519 0.0103 

 0.9562 0.0093 

 0.9607 0.0083 

 0.9654 0.0073 

 0.9701 0.0063 

 0.9745 0.0054 

 0.9796 0.0043 

 0.9850 0.0032 

 0.9911 0.0019 

 0.9964 0.0007 

 1 0.0000 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

NASA/TM—2002-211700 352
0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.1-0.2

0.20.10.0 Y/C

Fig. B-4 Commercial Transport Tail Section 

NASA/TM—2002-211700 353
Table B-4 Coordinates of Commercial Transport Tail Section 

Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

1.0000 -0.0096 0.4474 -0.0542 0.0054 -0.0118 0.0000 0.0003 0.4170 0.0334 0.9810 -0.0071 

0.9908 -0.0105 0.4340 -0.0545 0.0031 -0.0089 0.0006 0.0034 0.4306 0.0332 0.9907 -0.0079 

0.9811 -0.0113 0.4205 -0.0548 0.0014 -0.0057 0.0026 0.0066 0.4441 0.0330 1.0000 -0.0086 

0.9709 -0.0122 0.4071 -0.0551 0.0003 -0.0027 0.0055 0.0086 0.4576 0.0326 

0.9602 -0.0132 0.3936 -0.0553 0.0091 0.0106 0.4712 0.0323 

0.9491 -0.0142 0.3802 -0.0555 0.0131 0.0124 0.4847 0.0319 

0.9377 -0.0153 0.3667 -0.0557 0.0175 0.0140 0.4982 0.0314 

0.9258 -0.0164 0.3533 -0.0557 0.0222 0.0155 0.5117 0.0309 

0.9137 -0.0175 0.3399 -0.0558 0.0273 0.0168 0.5252 0.0303 

0.9013 -0.0187 0.3265 -0.0558 0.0328 0.0180 0.5387 0.0297 

0.8886 -0.0199 0.3131 -0.0558 0.0386 0.0192 0.5523 0.0290 

0.8758 -0.0212 0.2998 -0.0558 0.0448 0.0203 0.5658 0.0283 

0.8628 -0.0225 0.2865 -0.0557 0.0514 0.0214 0.5793 0.0275 

0.8498 -0.0237 0.2733 -0.0557 0.0585 0.0224 0.5928 0.0267 

0.8366 -0.0250 0.2602 -0.0555 0.0660 0.0234 0.6063 0.0258 

0.8233 -0.0264 0.2472 -0.0553 0.0739 0.0243 0.6198 0.0248 

0.8100 -0.0277 0.2342 -0.0549 0.0823 0.0252 0.6333 0.0239 

0.7967 -0.0290 0.2214 -0.0544 0.0912 0.0261 0.6468 0.0228 

0.7833 -0.0303 0.2087 -0.0539 0.1006 0.0269 0.6604 0.0218 

0.7699 -0.0317 0.1962 -0.0532 0.1105 0.0277 0.6739 0.0207 

0.7565 -0.0330 0.1838 -0.0525 0.1208 0.0284 0.6874 0.0196 

0.7430 -0.0343 0.1717 -0.0516 0.1315 0.0291 0.7009 0.0184 

0.7296 -0.0356 0.1598 -0.0508 0.1427 0.0297 0.7144 0.0172 

0.7162 -0.0369 0.1482 -0.0498 0.1542 0.0303 0.7280 0.0160 

0.7027 -0.0381 0.1369 -0.0487 0.1661 0.0308 0.7415 0.0148 

0.6893 -0.0393 0.1260 -0.0476 0.1782 0.0313 0.7550 0.0135 

0.6759 -0.0405 0.1154 -0.0464 0.1906 0.0317 0.7685 0.0123 

0.6624 -0.0417 0.1053 -0.0451 0.2033 0.0320 0.7820 0.0110 

0.6490 -0.0428 0.0957 -0.0437 0.2161 0.0323 0.7954 0.0097 

0.6356 -0.0439 0.0865 -0.0422 0.2291 0.0326 0.8089 0.0085 

0.6221 -0.0450 0.0778 -0.0406 0.2422 0.0328 0.8223 0.0072 

0.6087 -0.0460 0.0695 -0.0390 0.2554 0.0330 0.8356 0.0060 

0.5953 -0.0469 0.0617 -0.0373 0.2687 0.0332 0.8489 0.0047 

0.5818 -0.0479 0.0544 -0.0354 0.2821 0.0334 0.8620 0.0035 

0.5684 -0.0487 0.0476 -0.0335 0.2955 0.0336 0.8751 0.0023 

0.5550 -0.0495 0.0412 -0.0315 0.3089 0.0337 0.8880 0.0011 

0.5415 -0.0503 0.0352 -0.0294 0.3224 0.0338 0.9007 0.0000 

0.5281 -0.0510 0.0297 -0.0273 0.3359 0.0339 0.9132 -0.0012 

0.5147 -0.0516 0.0245 -0.0250 0.3494 0.0339 0.9254 -0.0023 

0.5012 -0.0522 0.0198 -0.0227 0.3629 0.0339 0.9373 -0.0033 

0.4878 -0.0528 0.0155 -0.0202 0.3764 0.0339 0.9488 -0.0043 

0.4743 -0.0533 0.0117 -0.0175 0.3900 0.0338 0.9600 -0.0053 

0.4609 -0.0538 0.0083 -0.0148 0.4042 0.0336 0.4170 0.0334 

NASA/TM—2002-211700 354
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.1-0.2

0

0.20.1

Y/C

Fig. B-5 NLF(1)-0414 Airfoil (c = 36 in.) 

NASA/TM—2002-211700 355
Table B-5 Coordinates of 36-inch NLF(1)-0414 Airfoil 

Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

1.0000 -0.0275 0.7548 -0.0401 0.5101 -0.0600 0.0000 0.0008 0.0617 0.0425 0.6008 0.0733 

0.9943 -0.0271 0.7492 -0.0412 0.5044 -0.0600 0.0001 0.0018 0.0667 0.0440 0.6185 0.0712 

0.9886 -0.0269 0.7436 -0.0423 0.4987 -0.0600 0.0002 0.0028 0.0717 0.0454 0.6303 0.0697 

0.9829 -0.0267 0.7380 -0.0435 0.4930 -0.0600 0.0004 0.0038 0.0768 0.0467 0.6454 0.0675 

0.9771 -0.0265 0.7324 -0.0448 0.4872 -0.0599 0.0006 0.0048 0.0818 0.0480 0.6602 0.0651 

0.9714 -0.0263 0.7268 -0.0460 0.4815 -0.0599 0.0008 0.0057 0.0869 0.0493 0.6750 0.0625 

0.9657 -0.0262 0.7212 -0.0472 0.4758 -0.0598 0.0011 0.0067 0.0932 0.0508 0.6903 0.0594 

0.9600 -0.0260 0.7156 -0.0483 0.4701 -0.0597 0.0014 0.0076 0.0996 0.0523 0.7053 0.0560 

0.9542 -0.0259 0.7100 -0.0494 0.4644 -0.0597 0.0018 0.0086 0.1088 0.0542 0.7188 0.0525 

0.9485 -0.0258 0.7043 -0.0503 0.4586 -0.0596 0.0021 0.0095 0.1191 0.0563 0.7347 0.0477 

0.9428 -0.0257 0.6987 -0.0511 0.4529 -0.0595 0.0026 0.0104 0.1301 0.0584 0.7528 0.0416 

0.9371 -0.0256 0.6930 -0.0519 0.4472 -0.0594 0.0031 0.0113 0.1418 0.0605 0.7746 0.0337 

0.9314 -0.0256 0.6873 -0.0525 0.4415 -0.0593 0.0036 0.0121 0.1543 0.0626 0.7971 0.0254 

0.9256 -0.0255 0.6816 -0.0532 0.4357 -0.0592 0.0041 0.0130 0.1639 0.0641 0.8208 0.0170 

0.9199 -0.0255 0.6759 -0.0537 0.4300 -0.0590 0.0047 0.0138 0.1721 0.0653 0.8434 0.0094 

0.9142 -0.0256 0.6702 -0.0543 0.4243 -0.0589 0.0053 0.0146 0.1844 0.0671 0.8672 0.0020 

0.9085 -0.0256 0.6645 -0.0548 0.4186 -0.0587 0.0059 0.0153 0.1938 0.0684 0.8950 -0.0058 

0.9027 -0.0257 0.6588 -0.0553 0.4129 -0.0586 0.0066 0.0161 0.2061 0.0700 0.9263 -0.0135 

0.8970 -0.0258 0.6531 -0.0557 0.4071 -0.0584 0.0073 0.0168 0.2200 0.0717 0.9629 -0.0211 

0.8913 -0.0260 0.6474 -0.0561 0.4014 -0.0582 0.0080 0.0175 0.2329 0.0731 1.0000 -0.0271 

0.8856 -0.0262 0.6417 -0.0565 0.3957 -0.0580 0.0087 0.0182 0.2468 0.0745 

0.8799 -0.0264 0.6360 -0.0569 0.3900 -0.0578 0.0095 0.0189 0.2561 0.0754 

0.8741 -0.0267 0.6303 -0.0572 0.3843 -0.0576 0.0102 0.0195 0.2658 0.0762 

0.8684 -0.0269 0.6246 -0.0575 0.3785 -0.0574 0.0110 0.0202 0.2803 0.0774 

0.8627 -0.0273 0.6188 -0.0578 0.3728 -0.0571 0.0118 0.0208 0.2955 0.0785 

0.8570 -0.0276 0.6131 -0.0580 0.3671 -0.0569 0.0126 0.0214 0.3092 0.0794 

0.8513 -0.0280 0.6074 -0.0583 0.3614 -0.0566 0.0134 0.0220 0.3237 0.0802 

0.8456 -0.0285 0.6017 -0.0585 0.3557 -0.0564 0.0142 0.0225 0.3390 0.0809 

0.8399 -0.0290 0.5960 -0.0587 0.3500 -0.0561 0.0151 0.0231 0.3543 0.0815 

0.8342 -0.0295 0.5902 -0.0589 0.3442 -0.0558 0.0159 0.0236 0.3701 0.0820 

0.8285 -0.0300 0.5845 -0.0590 0.3385 -0.0555 0.0168 0.0241 0.3836 0.0823 

0.8228 -0.0306 0.5788 -0.0592 0.3328 -0.0552 0.0176 0.0246 0.3945 0.0825 

0.8171 -0.0312 0.5731 -0.0593 0.3271 -0.0549 0.0185 0.0251 0.4056 0.0826 

0.8114 -0.0318 0.5674 -0.0595 0.3214 -0.0545 0.0194 0.0256 0.4164 0.0827 

0.8057 -0.0325 0.5616 -0.0596 0.3157 -0.0542 0.0206 0.0263 0.4279 0.0827 

0.8001 -0.0332 0.5559 -0.0597 0.3100 -0.0539 0.0223 0.0272 0.4451 0.0825 

0.7944 -0.0339 0.5502 -0.0598 0.3042 -0.0535 0.0248 0.0285 0.4632 0.0822 

0.7887 -0.0347 0.5445 -0.0599 0.2985 -0.0532 0.0282 0.0301 0.4839 0.0816 

0.7830 -0.0355 0.5388 -0.0599 0.2928 -0.0528 0.0335 0.0325 0.4993 0.0810 

0.7774 -0.0363 0.5330 -0.0600 0.2871 -0.0524 0.0403 0.0352 0.5205 0.0800 

0.7717 -0.0372 0.5273 -0.0600 0.2814 -0.0520 0.0450 0.0370 0.5375 0.0789 

0.7661 -0.0381 0.5216 -0.0600 0.2757 -0.0516 0.0496 0.0386 0.5578 0.0774 

0.7604 -0.0391 0.5159 -0.0600 0.2700 -0.0512 0.0566 0.0409 0.5763 0.0758 

NASA/TM—2002-211700 356
Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

0.2643 -0.0508 0.0216 -0.0170 

0.2586 -0.0504 0.0197 -0.0164 

0.2529 -0.0499 0.0184 -0.0159 

0.2472 -0.0495 0.0174 -0.0156 

0.2415 -0.0490 0.0165 -0.0152 

0.2358 -0.0486 0.0156 -0.0149 

0.2300 -0.0481 0.0146 -0.0145 

0.2243 -0.0476 0.0137 -0.0142 

0.2186 -0.0471 0.0128 -0.0138 

0.2129 -0.0466 0.0119 -0.0134 

0.2072 -0.0461 0.0110 -0.0130 

0.2015 -0.0455 0.0101 -0.0125 

0.1959 -0.0450 0.0092 -0.0121 

0.1902 -0.0444 0.0083 -0.0116 

0.1845 -0.0438 0.0074 -0.0111 

0.1788 -0.0432 0.0065 -0.0106 

0.1731 -0.0426 0.0057 -0.0101 

0.1674 -0.0420 0.0049 -0.0095 

0.1617 -0.0414 0.0041 -0.0089 

0.1560 -0.0407 0.0033 -0.0083 

0.1503 -0.0401 0.0026 -0.0076 

0.1446 -0.0394 0.0020 -0.0068 

0.1390 -0.0387 0.0014 -0.0060 

0.1333 -0.0380 0.0010 -0.0051 

0.1276 -0.0372 0.0006 -0.0041 

0.1219 -0.0365 0.0004 -0.0032 

0.1163 -0.0357 0.0002 -0.0022 

0.1106 -0.0349 0.0001 -0.0012 

0.1049 -0.0341 0.0000 -0.0002 

0.0993 -0.0332 

0.0936 -0.0323 

0.0875 -0.0314 

0.0814 -0.0304 

0.0753 -0.0293 

0.0693 -0.0282 

0.0632 -0.0271 

0.0571 -0.0259 

0.0511 -0.0246 

0.0451 -0.0233 

0.0390 -0.0219 

0.0331 -0.0203 

0.0279 -0.0189 

0.0242 -0.0178 

NASA/TM—2002-211700 357
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

X/C

-0.1

-0.2

0

0.2

0.1

Y/C

Fig. B-6 NLF(1)-0414 Airfoil (c = 48 in.) 

NASA/TM—2002-211700 358
Table B-6a Coordinates of 48-in NLF(1)-0414 Airfoil (Main Element) 

Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

0.7830 -0.0355 0.0001 0.0022 

0.7499 -0.0411 0.0019 0.0090 

0.7249 -0.0464 0.0052 0.0144 

0.6999 -0.0509 0.0101 0.0195 

0.6749 -0.0539 0.0150 0.0231 

0.6499 -0.0560 0.0201 0.0261 

0.6248 -0.0575 0.0251 0.0287 

0.5999 -0.0586 0.0301 0.0310 

0.5500 -0.0598 0.0400 0.0351 

0.4999 -0.0600 0.0500 0.0387 

0.4500 -0.0595 0.0600 0.0420 

0.4001 -0.0582 0.0751 0.0463 

0.3500 -0.0561 0.1000 0.0524 

0.3000 -0.0533 0.1500 0.0619 

0.2500 -0.0497 0.2000 0.0693 

0.1999 -0.0454 0.2500 0.0749 

0.1501 -0.0400 0.3000 0.0789 

0.1001 -0.0334 0.3500 0.0814 

0.0750 -0.0293 0.4000 0.0826 

0.0600 -0.0265 0.4500 0.0825 

0.0500 -0.0244 0.5000 0.0810 

0.0400 -0.0221 0.5501 0.0781 

0.0301 -0.0196 0.6000 0.0735 

0.0250 -0.0181 0.6250 0.0704 

0.0201 -0.0165 0.6500 0.0668 

0.0151 -0.0147 0.6750 0.0626 

0.0101 -0.0126 0.7000 0.0573 

0.0053 -0.0099 0.7250 0.0508 

0.0019 -0.0067 0.7500 0.0426 

0.0001 -0.0019 0.7836 0.0303 

 

 

 

 

 

 

 

 

 

 

 

 

 

NASA/TM—2002-211700 359
Table B-6b Coordinates of 48-in NLF(1)-0414 Airfoil (Flap Element) 

Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

1.0000 -0.0273 0.7510 0.0058 

0.9700 -0.0269 0.7531 0.0166 

0.9625 -0.0266 0.7551 0.0153 

0.9500 -0.0263 0.7604 0.0216 

0.9370 -0.0260 0.7659 0.0286 

0.9208 -0.0259 0.7671 0.0265 

0.9000 -0.0260 0.7748 0.0296 

0.8789 -0.0267 0.7836 0.0303 

0.8638 -0.0274 0.7903 0.0280 

0.8499 -0.0283 0.8001 0.0244 

0.8420 -0.0289 0.8123 0.0201 

0.8263 -0.0304 0.8274 0.0148 

0.8112 -0.0319 0.8274 0.0148 

0.8000 -0.0333 0.8410 0.0103 

0.7889 -0.0347 0.8500 0.0074 

0.7830 -0.0355 0.8674 0.0021 

0.7748 -0.0344 0.8807 -0.0017 

0.7671 -0.0313 0.9000 -0.0068 

0.7659 -0.0335 0.9210 -0.0119 

0.7604 -0.0265 0.9345 -0.0149 

0.7551 -0.0201 0.9500 -0.0181 

0.7477 -0.0046 0.9613 -0.0202 

0.7531 -0.0214 0.9700 -0.0218 

0.7516 -0.0126 1.0000 -0.0273 

0.7501 -0.0045 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

NASA/TM—2002-211700 360
0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.1-0.2

0.20.10.0 Y/C

Fig. B-7 NACA 64A008 finite swept tail (c = 36 in.) 

NASA/TM—2002-211700 361
Table B-7 Coordinates of NACA 64A008 Finite Swept Tail 

Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

1.0000 -0.0018 0.7872 -0.0181 0.5590 -0.0348 0.0000 0.0004 0.0913 0.0246 0.3025 0.0387 

0.9943 -0.0020 0.7817 -0.0185 0.5535 -0.0351 0.0003 0.0014 0.0961 0.0251 0.3078 0.0389 

0.9888 -0.0023 0.7761 -0.0190 0.5481 -0.0353 0.0007 0.0023 0.1009 0.0257 0.3132 0.0390 

0.9834 -0.0025 0.7703 -0.0195 0.5428 -0.0356 0.0012 0.0031 0.1058 0.0262 0.3186 0.0391 

0.9782 -0.0028 0.7658 -0.0199 0.5374 -0.0359 0.0019 0.0039 0.1107 0.0268 0.3239 0.0393 

0.9731 -0.0030 0.7603 -0.0203 0.5319 -0.0362 0.0026 0.0046 0.1156 0.0273 0.3292 0.0394 

0.9681 -0.0033 0.7542 -0.0208 0.5265 -0.0364 0.0033 0.0053 0.1206 0.0278 0.3346 0.0395 

0.9633 -0.0036 0.7485 -0.0213 0.5211 -0.0367 0.0041 0.0059 0.1256 0.0283 0.3400 0.0396 

0.9585 -0.0038 0.7427 -0.0218 0.5157 -0.0369 0.0049 0.0064 0.1307 0.0288 0.3454 0.0397 

0.9537 -0.0041 0.7371 -0.0222 0.5103 -0.0371 0.0058 0.0069 0.1358 0.0292 0.3507 0.0397 

0.9491 -0.0044 0.7313 -0.0227 0.5049 -0.0374 0.0067 0.0074 0.1409 0.0297 0.3560 0.0398 

0.9448 -0.0048 0.7257 -0.0232 0.4995 -0.0376 0.0076 0.0078 0.1461 0.0301 0.3613 0.0399 

0.9402 -0.0051 0.7198 -0.0236 0.4943 -0.0378 0.0085 0.0082 0.1512 0.0306 0.3665 0.0399 

0.9358 -0.0055 0.7139 -0.0241 0.4890 -0.0380 0.0094 0.0086 0.1563 0.0310 0.3717 0.0399 

0.9315 -0.0058 0.7081 -0.0246 0.4839 -0.0382 0.0103 0.0090 0.1614 0.0314 0.3769 0.0400 

0.9267 -0.0062 0.7027 -0.0250 0.4789 -0.0384 0.0113 0.0094 0.1666 0.0318 0.3821 0.0400 

0.9216 -0.0067 0.6971 -0.0254 0.4736 -0.0385 0.0122 0.0097 0.1717 0.0322 0.3873 0.0400 

0.9164 -0.0071 0.6915 -0.0259 0.4682 -0.0387 0.0132 0.0101 0.1768 0.0326 0.3925 0.0400 

0.9104 -0.0077 0.6858 -0.0263 0.4631 -0.0389 0.0141 0.0104 0.1820 0.0329 0.3976 0.0400 

0.9045 -0.0082 0.6800 -0.0268 0.4579 -0.0390 0.0150 0.0107 0.1871 0.0333 0.4026 0.0400 

0.8993 -0.0086 0.6743 -0.0272 0.4531 -0.0391 0.0160 0.0110 0.1921 0.0336 0.4077 0.0399 

0.8941 -0.0091 0.6687 -0.0276 0.4480 -0.0393 0.0169 0.0113 0.1972 0.0340 0.4127 0.0399 

0.8889 -0.0095 0.6630 -0.0280 0.4428 -0.0394 0.0179 0.0116 0.2024 0.0343 0.4179 0.0398 

0.8837 -0.0100 0.6576 -0.0284 0.4376 -0.0395 0.0189 0.0119 0.2076 0.0346 0.4230 0.0398 

0.8785 -0.0104 0.6522 -0.0288 0.4323 -0.0396 0.0202 0.0123 0.2128 0.0349 0.4282 0.0397 

0.8737 -0.0108 0.6469 -0.0292 0.4271 -0.0397 0.0221 0.0128 0.2181 0.0352 0.4384 0.0395 

0.8683 -0.0113 0.6414 -0.0296 0.4219 -0.0398 0.0248 0.0135 0.2234 0.0355 0.4333 0.0396 

0.8624 -0.0118 0.6360 -0.0300 0.4167 -0.0398 0.0285 0.0144 0.2287 0.0358 0.4435 0.0394 

0.8562 -0.0123 0.6305 -0.0303 0.4116 -0.0399 0.0326 0.0153 0.2340 0.0361 0.4486 0.0392 

0.8501 -0.0128 0.6249 -0.0307 0.4064 -0.0399 0.0367 0.0162 0.2393 0.0363 0.4538 0.0391 

0.8450 -0.0132 0.6193 -0.0311 0.4013 -0.0400 0.0410 0.0170 0.2446 0.0366 0.4590 0.0390 

0.8410 -0.0135 0.6138 -0.0315 0.3961 -0.0400 0.0453 0.0178 0.2499 0.0368 0.4637 0.0388 

0.8362 -0.0139 0.6082 -0.0318 0.3910 -0.0400 0.0498 0.0186 0.2551 0.0370 0.4683 0.0387 

0.8315 -0.0143 0.6028 -0.0322 0.3857 -0.0400 0.0543 0.0193 0.2604 0.0373 0.4735 0.0385 

0.8262 -0.0148 0.5974 -0.0325 0.3805 -0.0400 0.0587 0.0201 0.2657 0.0375 0.4787 0.0384 

0.8205 -0.0152 0.5921 -0.0328 0.3753 -0.0400 0.0631 0.0207 0.2709 0.0377 0.4835 0.0382 

0.8150 -0.0157 0.5866 -0.0332 0.3701 -0.0399 0.0678 0.0214 0.2762 0.0379 0.4885 0.0380 

0.8094 -0.0162 0.5811 -0.0335 0.3649 -0.0399 0.0722 0.0221 0.2815 0.0381 0.4933 0.0378 

0.8039 -0.0167 0.5756 -0.0338 0.3596 -0.0398 0.0770 0.0227 0.2867 0.0382 0.4981 0.0376 

0.7983 -0.0171 0.5701 -0.0341 0.3543 -0.0398 0.0817 0.0233 0.2920 0.0384 0.5034 0.0374 

0.7928 -0.0176 0.5645 -0.0345 0.3490 -0.0397 0.0865 0.0240 0.2972 0.0386 0.5085 0.0372 

NASA/TM—2002-211700 362
Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

0.3436 -0.0396 0.0989 -0.0255 0.5137 0.0370 0.7520 0.0210 0.9845 0.0025 

0.3382 -0.0395 0.0941 -0.0249 0.5190 0.0368 0.7574 0.0206 0.9897 0.0022 

0.3328 -0.0394 0.0893 -0.0243 0.5241 0.0365 0.7627 0.0201 0.9950 0.0020 

0.3275 -0.0393 0.0846 -0.0237 0.5293 0.0363 0.7683 0.0196 1.0000 0.0018 

0.3221 -0.0392 0.0798 -0.0231 0.5345 0.0360 0.7738 0.0192 

0.3168 -0.0391 0.0751 -0.0225 0.5397 0.0358 0.7794 0.0187 

0.3114 -0.0390 0.0706 -0.0218 0.5448 0.0355 0.7850 0.0182 

0.3061 -0.0388 0.0661 -0.0212 0.5499 0.0352 0.7906 0.0178 

0.3007 -0.0387 0.0620 -0.0206 0.5542 0.0350 0.7962 0.0173 

0.2954 -0.0385 0.0575 -0.0199 0.5594 0.0347 0.8018 0.0168 

0.2902 -0.0384 0.0530 -0.0191 0.5648 0.0344 0.8075 0.0164 

0.2849 -0.0382 0.0486 -0.0184 0.5701 0.0341 0.8131 0.0159 

0.2797 -0.0380 0.0443 -0.0176 0.5755 0.0338 0.8187 0.0154 

0.2744 -0.0378 0.0400 -0.0168 0.5809 0.0335 0.8255 0.0148 

0.2691 -0.0376 0.0358 -0.0160 0.5858 0.0332 0.8310 0.0144 

0.2637 -0.0374 0.0317 -0.0151 0.5912 0.0329 0.8360 0.0139 

0.2585 -0.0372 0.0277 -0.0142 0.5965 0.0326 0.8416 0.0135 

0.2532 -0.0370 0.0240 -0.0133 0.6015 0.0322 0.8474 0.0130 

0.2480 -0.0367 0.0213 -0.0126 0.6068 0.0319 0.8530 0.0125 

0.2426 -0.0365 0.0194 -0.0121 0.6123 0.0316 0.8587 0.0121 

0.2214 -0.0354 0.0181 -0.0117 0.6177 0.0312 0.8642 0.0116 

0.2161 -0.0351 0.0171 -0.0114 0.6231 0.0308 0.8698 0.0111 

0.2109 -0.0348 0.0162 -0.0111 0.6286 0.0305 0.8748 0.0107 

0.2057 -0.0345 0.0152 -0.0108 0.6340 0.0301 0.8801 0.0103 

0.2005 -0.0342 0.0143 -0.0105 0.6396 0.0297 0.8857 0.0098 

0.1953 -0.0338 0.0133 -0.0101 0.6449 0.0293 0.8909 0.0094 

0.1902 -0.0335 0.0124 -0.0098 0.6501 0.0290 0.8960 0.0089 

0.1850 -0.0332 0.0115 -0.0094 0.6554 0.0286 0.9014 0.0085 

0.1798 -0.0328 0.0105 -0.0091 0.6610 0.0282 0.9068 0.0080 

0.1747 -0.0324 0.0096 -0.0087 0.6664 0.0278 0.9142 0.0073 

0.1695 -0.0320 0.0087 -0.0083 0.6718 0.0274 0.9195 0.0068 

0.1644 -0.0316 0.0078 -0.0079 0.6774 0.0270 0.9247 0.0064 

0.1592 -0.0312 0.0069 -0.0075 0.6830 0.0265 0.9293 0.0060 

0.1541 -0.0308 0.0060 -0.0070 0.6884 0.0261 0.9335 0.0056 

0.1489 -0.0304 0.0051 -0.0065 0.6939 0.0257 0.9378 0.0053 

0.1438 -0.0299 0.0043 -0.0060 0.6992 0.0253 0.9422 0.0050 

0.1387 -0.0295 0.0035 -0.0054 0.7047 0.0248 0.9465 0.0046 

0.1336 -0.0290 0.0027 -0.0047 0.7104 0.0244 0.9506 0.0043 

0.1285 -0.0286 0.0020 -0.0040 0.7163 0.0239 0.9553 0.0040 

0.1235 -0.0281 0.0013 -0.0033 0.7219 0.0235 0.9600 0.0037 

0.1185 -0.0276 0.0008 -0.0024 0.7278 0.0230 0.9648 0.0035 

0.1136 -0.0271 0.0003 -0.0016 0.7340 0.0225 0.9697 0.0032 

0.1087 -0.0266 0.0001 -0.0006 0.7399 0.0220 0.9746 0.0030 

0.1038 -0.0260 0.7460 0.0215 0.9794 0.0027 

NASA/TM—2002-211700 363
0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

X/C

-0.1-0.2

0.20.10.0 Y/C

Fig. B-7 Business Jet Horizontal Tail 

NASA/TM—2002-211700 364
Table B-7 Coordinates of Business Jet Horizontal Tail 

Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

1.0000 0.0000 0.9874 -0.0012 0.8419 -0.0135 0.0102 0.0010 0.1294 0.0259 0.8448 0.0132 

1.0000 -0.0001 0.9864 -0.0013 0.8306 -0.0144 0.0122 0.0020 0.1362 0.0267 0.8554 0.0123 

1.0000 -0.0002 0.9853 -0.0014 0.8186 -0.0154 0.0142 0.0029 0.1435 0.0275 0.8652 0.0115 

0.9999 -0.0002 0.9842 -0.0015 0.8057 -0.0165 0.0163 0.0038 0.1512 0.0283 0.8743 0.0107 

0.9998 -0.0002 0.9830 -0.0016 0.7919 -0.0177 0.0184 0.0046 0.1597 0.0291 0.8829 0.0100 

0.9997 -0.0002 0.9817 -0.0017 0.7771 -0.0189 0.0205 0.0054 0.1688 0.0300 0.8909 0.0093 

0.9996 -0.0002 0.9804 -0.0018 0.7613 -0.0202 0.0227 0.0062 0.1787 0.0308 0.8983 0.0087 

0.9994 -0.0002 0.9789 -0.0020 0.7443 -0.0216 0.0249 0.0069 0.1895 0.0317 0.9052 0.0081 

0.9993 -0.0002 0.9773 -0.0021 0.7260 -0.0231 0.0272 0.0076 0.2014 0.0326 0.9117 0.0076 

0.9991 -0.0003 0.9756 -0.0022 0.7065 -0.0247 0.0295 0.0083 0.2146 0.0336 0.9177 0.0071 

0.9990 -0.0003 0.9739 -0.0024 0.6855 -0.0263 0.0319 0.0090 0.2293 0.0345 0.9233 0.0066 

0.9988 -0.0003 0.9719 -0.0025 0.6630 -0.0280 0.0343 0.0096 0.2457 0.0355 0.9286 0.0062 

0.9986 -0.0003 0.9699 -0.0027 0.6389 -0.0298 0.0368 0.0103 0.2642 0.0365 0.9335 0.0058 

0.9984 -0.0003 0.9677 -0.0029 0.6129 -0.0315 0.0393 0.0110 0.2853 0.0375 0.9380 0.0054 

0.9982 -0.0003 0.9653 -0.0031 0.5851 -0.0333 0.0419 0.0116 0.3096 0.0384 0.9423 0.0050 

0.9980 -0.0003 0.9628 -0.0033 0.5551 -0.0350 0.0445 0.0122 0.3379 0.0393 0.9463 0.0047 

0.9978 -0.0004 0.9601 -0.0035 0.5230 -0.0366 0.0472 0.0129 0.3712 0.0398 0.9500 0.0044 

0.9975 -0.0004 0.9573 -0.0038 0.4884 -0.0380 0.0500 0.0135 0.4112 0.0399 0.9534 0.0041 

0.9972 -0.0004 0.9542 -0.0040 0.4512 -0.0391 0.0529 0.0141 0.4512 0.0392 0.9566 0.0038 

0.9969 -0.0004 0.9509 -0.0043 0.4112 -0.0398 0.0558 0.0147 0.4885 0.0380 0.9596 0.0036 

0.9966 -0.0005 0.9474 -0.0046 0.3712 -0.0401 0.0589 0.0153 0.5232 0.0366 0.9625 0.0033 

0.9963 -0.0005 0.9436 -0.0049 0.3379 -0.0401 0.0620 0.0160 0.5555 0.0349 0.9651 0.0031 

0.9959 -0.0005 0.9395 -0.0053 0.3096 -0.0399 0.0653 0.0166 0.5857 0.0332 0.9675 0.0029 

0.9956 -0.0006 0.9352 -0.0056 0.2853 -0.0396 0.0687 0.0172 0.6137 0.0315 0.9698 0.0027 

0.9951 -0.0006 0.9306 -0.0060 0.2641 -0.0393 0.0722 0.0178 0.6399 0.0297 0.9719 0.0025 

0.9947 -0.0006 0.9257 -0.0064 0.2456 -0.0389 0.0758 0.0185 0.6643 0.0279 0.9739 0.0024 

0.9942 -0.0007 0.9204 -0.0069 0.2292 -0.0385 0.0796 0.0191 0.6870 0.0262 0.8448 0.0132 

0.9937 -0.0007 0.9147 -0.0073 0.2145 -0.0381 0.0835 0.0197 0.7082 0.0246 0.8554 0.0123 

0.9932 -0.0008 0.9086 -0.0079 0.2013 -0.0378 0.0876 0.0204 0.7280 0.0230 0.8652 0.0115 

0.9926 -0.0008 0.9021 -0.0084 0.1893 -0.0374 0.0920 0.0210 0.7464 0.0215 0.8743 0.0107 

0.9920 -0.0009 0.8952 -0.0090 0.1785 -0.0370 0.0965 0.0217 0.7636 0.0200 0.8829 0.0100 

0.9914 -0.0009 0.8877 -0.0096 0.1685 -0.0366 0.1012 0.0224 0.7796 0.0187 0.8909 0.0093 

0.9907 -0.0010 0.8798 -0.0103 0.1594 -0.0362 0.1063 0.0231 0.7945 0.0174 0.8983 0.0087 

0.9899 -0.0010 0.8713 -0.0110 0.1509 -0.0358 0.1115 0.0238 0.8084 0.0163 0.9052 0.0081 

0.9891 -0.0011 0.8621 -0.0118 0.1431 -0.0354 0.1172 0.0245 0.8214 0.0152 0.9117 0.0076 

0.9883 -0.0012 0.8523 -0.0126 0.1358 -0.0351 0.1231 0.0252 0.8335 0.0142 0.9177 0.0071 

1.0000 0.0000 0.9874 -0.0012 0.8419 -0.0135 0.0102 0.0010 0.1294 0.0259 0.9233 0.0066 

1.0000 -0.0001 0.9864 -0.0013 0.8306 -0.0144 0.0122 0.0020 0.1362 0.0267 0.9286 0.0062 

1.0000 -0.0002 0.9853 -0.0014 0.8186 -0.0154 0.0142 0.0029 0.1435 0.0275 0.9335 0.0058 

0.9999 -0.0002 0.9842 -0.0015 0.8057 -0.0165 0.0163 0.0038 0.1512 0.0283 0.9380 0.0054 

0.9998 -0.0002 0.9830 -0.0016 0.7919 -0.0177 0.0184 0.0046 0.1597 0.0291 0.9423 0.0050 

0.9997 -0.0002 0.9817 -0.0017 0.7771 -0.0189 0.0205 0.0054 0.1688 0.0300 0.9463 0.0047 

0.9996 -0.0002 0.9804 -0.0018 0.7613 -0.0202 0.0227 0.0062 0.1787 0.0308 0.9500 0.0044 

NASA/TM—2002-211700 365
Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

0.1290 -0.0347 0.0123 -0.0206 0.9757 0.0022 1.0000 0.0000 

0.1227 -0.0343 0.0102 -0.0198 0.9775 0.0021 

0.1167 -0.0340 0.0082 -0.0190 0.9791 0.0019 

0.1110 -0.0336 0.0062 -0.0180 0.9806 0.0018 

0.1057 -0.0333 0.0044 -0.0168 0.9820 0.0017 

0.1007 -0.0329 0.0027 -0.0154 0.9833 0.0016 

0.0959 -0.0325 0.0013 -0.0137 0.9845 0.0015 

0.0913 -0.0322 0.0003 -0.0118 0.9856 0.0014 

0.0870 -0.0318 0.0000 -0.0097 0.9867 0.0013 

0.0828 -0.0315 0.0006 -0.0076 0.9877 0.0012 

0.0788 -0.0311 0.0017 -0.0057 0.9886 0.0011 

0.0750 -0.0308 0.0031 -0.0039 0.9894 0.0011 

0.0713 -0.0304 0.0047 -0.0025 0.9902 0.0010 

0.0678 -0.0301 0.0064 -0.0012 0.9910 0.0009 

0.0644 -0.0297 0.0083 -0.0001 0.9917 0.0009 

0.0611 -0.0294 0.9923 0.0008 

0.0579 -0.0290 0.9929 0.0008 

0.0548 -0.0286 0.9935 0.0007 

0.0518 -0.0283 0.9940 0.0007 

0.0489 -0.0279 0.9945 0.0006 

0.0461 -0.0275 0.9950 0.0006 

0.0433 -0.0271 0.9954 0.0006 

0.0406 -0.0267 0.9958 0.0005 

0.0380 -0.0263 0.9962 0.0005 

0.0354 -0.0259 0.9965 0.0005 

0.0329 -0.0255 0.9969 0.0004 

0.1290 -0.0347 0.9972 0.0004 

0.1227 -0.0343 0.9975 0.0004 

0.1167 -0.0340 0.9977 0.0004 

0.1110 -0.0336 0.9980 0.0004 

0.1057 -0.0333 0.9982 0.0003 

0.1007 -0.0329 0.9984 0.0003 

0.0959 -0.0325 0.9986 0.0003 

0.0913 -0.0322 0.9988 0.0003 

0.0870 -0.0318 0.9990 0.0003 

0.0305 -0.0251 0.9993 0.0002 

0.0280 -0.0246 0.9994 0.0002 

0.0257 -0.0241 0.9996 0.0002 

0.0233 -0.0236 0.9997 0.0002 

0.0211 -0.0231 0.9998 0.0002 

0.0188 -0.0225 0.9999 0.0002 

0.0166 -0.0219 1.0000 0.0002 

0.0144 -0.0213 1.0000 0.0001 

NASA/TM—2002-211700 366
-0.2 -0.1 0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2

X/C

-0.1

-0.2

0.2

0.1

0.0 Y/C

Fig. B-8 Three-element High Lift System 

NASA/TM—2002-211700 367
Table B-8a Three-element High Lift System - Slat Element Coordinates 

Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

0.0188 0.0051 -0.0213 -0.0377 -0.0475 -0.1140 -0.0853 -0.0985 0.0091 -0.0023 

0.0184 0.0047 -0.0230 -0.0401 -0.0489 -0.1142 -0.0852 -0.0974 0.0103 -0.0014 

0.0181 0.0043 -0.0246 -0.0424 -0.0502 -0.1145 -0.0850 -0.0964 0.0114 -0.0005 

0.0177 0.0040 -0.0262 -0.0447 -0.0514 -0.1147 -0.0848 -0.0954 0.0124 0.0003 

0.0173 0.0035 -0.0278 -0.0471 -0.0526 -0.1149 -0.0845 -0.0944 0.0134 0.0010 

0.0169 0.0031 -0.0293 -0.0495 -0.0537 -0.1150 -0.0842 -0.0932 0.0142 0.0016 

0.0165 0.0027 -0.0307 -0.0518 -0.0548 -0.1152 -0.0838 -0.0920 0.0150 0.0022 

0.0160 0.0022 -0.0321 -0.0543 -0.0558 -0.1153 -0.0832 -0.0908 0.0157 0.0027 

0.0156 0.0017 -0.0334 -0.0567 -0.0567 -0.1154 -0.0827 -0.0894 0.0163 0.0032 

0.0151 0.0012 -0.0347 -0.0591 -0.0577 -0.1155 -0.0820 -0.0880 0.0169 0.0037 

0.0146 0.0006 -0.0359 -0.0616 -0.0585 -0.1156 -0.0812 -0.0864 0.0175 0.0041 

0.0141 0.0001 -0.0371 -0.0641 -0.0593 -0.1156 -0.0802 -0.0848 0.0179 0.0044 

0.0136 -0.0005 -0.0381 -0.0666 -0.0601 -0.1157 -0.0792 -0.0831 0.0184 0.0048 

0.0130 -0.0011 -0.0391 -0.0692 -0.0609 -0.1157 -0.0780 -0.0813 0.0188 0.0051 

0.0124 -0.0018 -0.0400 -0.0717 -0.0616 -0.1157 -0.0767 -0.0793 

0.0118 -0.0024 -0.0408 -0.0743 -0.0622 -0.1157 -0.0752 -0.0772 

0.0112 -0.0031 -0.0415 -0.0769 -0.0628 -0.1157 -0.0735 -0.0751 

0.0105 -0.0038 -0.0421 -0.0795 -0.0634 -0.1157 -0.0716 -0.0727 

0.0098 -0.0046 -0.0426 -0.0821 -0.0640 -0.1157 -0.0695 -0.0703 

0.0091 -0.0053 -0.0431 -0.0847 -0.0645 -0.1157 -0.0672 -0.0677 

0.0083 -0.0061 -0.0433 -0.0873 -0.0651 -0.1157 -0.0647 -0.0650 

0.0075 -0.0069 -0.0433 -0.0899 -0.0656 -0.1157 -0.0619 -0.0620 

0.0067 -0.0078 -0.0432 -0.0926 -0.0662 -0.1157 -0.0588 -0.0589 

0.0058 -0.0087 -0.0428 -0.0951 -0.0668 -0.1157 -0.0554 -0.0556 

0.0049 -0.0096 -0.0421 -0.0976 -0.0674 -0.1156 -0.0517 -0.0521 

0.0039 -0.0106 -0.0411 -0.1000 -0.0680 -0.1156 -0.0476 -0.0484 

0.0029 -0.0116 -0.0399 -0.1023 -0.0686 -0.1155 -0.0431 -0.0444 

0.0018 -0.0126 -0.0383 -0.1043 -0.0692 -0.1155 -0.0382 -0.0401 

0.0007 -0.0137 -0.0363 -0.1059 -0.0698 -0.1154 -0.0329 -0.0356 

-0.0004 -0.0148 -0.0341 -0.1071 -0.0704 -0.1153 -0.0280 -0.0315 

-0.0016 -0.0160 -0.0317 -0.1079 -0.0711 -0.1151 -0.0236 -0.0278 

-0.0028 -0.0172 -0.0292 -0.1084 -0.0717 -0.1150 -0.0195 -0.0245 

-0.0041 -0.0185 -0.0267 -0.1087 -0.0724 -0.1148 -0.0157 -0.0215 

-0.0055 -0.0198 -0.0291 -0.1094 -0.0731 -0.1147 -0.0123 -0.0188 

-0.0069 -0.0212 -0.0314 -0.1100 -0.0737 -0.1145 -0.0092 -0.0163 

-0.0083 -0.0227 -0.0336 -0.1106 -0.0744 -0.1142 -0.0063 -0.0141 

-0.0098 -0.0242 -0.0357 -0.1112 -0.0751 -0.1140 -0.0037 -0.0121 

-0.0113 -0.0258 -0.0376 -0.1117 -0.0758 -0.1137 -0.0014 -0.0103 

-0.0129 -0.0275 -0.0395 -0.1122 -0.0765 -0.1134 0.0008 -0.0086 

-0.0145 -0.0293 -0.0413 -0.1126 -0.0772 -0.1131 0.0028 -0.0071 

-0.0162 -0.0313 -0.0429 -0.1130 -0.0779 -0.1127 0.0046 -0.0057 

-0.0179 -0.0333 -0.0445 -0.1134 -0.0785 -0.1123 0.0062 -0.0045 

-0.0196 -0.0355 -0.0461 -0.1137 -0.0792 -0.1119 0.0077 -0.0033 

NASA/TM—2002-211700 368
Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

-0.0799 -0.1114 

-0.0806 -0.1109 

-0.0812 -0.1103 

-0.0818 -0.1097 

-0.0824 -0.1090 

-0.0830 -0.1083 

-0.0834 -0.1075 

-0.0839 -0.1067 

-0.0843 -0.1059 

-0.0846 -0.1050 

-0.0849 -0.1040 

-0.0851 -0.1030 

-0.0853 -0.1020 

-0.0854 -0.1009 

-0.0854 -0.0996 

 

NASA/TM—2002-211700 369
Table B-8b Three-element High Lift System - Main Element Coordinates 

Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

0.8740 0.0309 0.7073 0.0320 0.5654 -0.0404 0.0497 0.0000 0.5322 0.0610 

0.8729 0.0310 0.7047 0.0320 0.5419 -0.0436 0.0504 0.0010 0.5603 0.0602 

0.8716 0.0311 0.7022 0.0320 0.5145 -0.0466 0.0513 0.0020 0.5862 0.0592 

0.8702 0.0311 0.6999 0.0320 0.4828 -0.0497 0.0522 0.0032 0.6100 0.0582 

0.8686 0.0312 0.6999 0.0297 0.4459 -0.0521 0.0533 0.0044 0.6320 0.0570 

0.8669 0.0313 0.6999 0.0273 0.4033 -0.0540 0.0545 0.0056 0.6522 0.0558 

0.8650 0.0314 0.6999 0.0246 0.3538 -0.0544 0.0558 0.0070 0.6708 0.0546 

0.8628 0.0314 0.6999 0.0218 0.3113 -0.0540 0.0573 0.0084 0.6879 0.0533 

0.8604 0.0315 0.6999 0.0188 0.2747 -0.0531 0.0590 0.0098 0.7037 0.0521 

0.8578 0.0316 0.6999 0.0156 0.2433 -0.0515 0.0609 0.0114 0.7183 0.0509 

0.8549 0.0317 0.6999 0.0122 0.2163 -0.0500 0.0630 0.0130 0.7316 0.0496 

0.8516 0.0318 0.6999 0.0085 0.1930 -0.0483 0.0653 0.0147 0.7439 0.0484 

0.8480 0.0318 0.6999 0.0050 0.1731 -0.0466 0.0679 0.0165 0.7553 0.0473 

0.8440 0.0319 0.6999 0.0017 0.1559 -0.0450 0.0708 0.0183 0.7657 0.0462 

0.8395 0.0319 0.6999 -0.0015 0.1412 -0.0435 0.0740 0.0202 0.7753 0.0451 

0.8346 0.0320 0.6999 -0.0045 0.1285 -0.0420 0.0775 0.0222 0.7842 0.0441 

0.8291 0.0320 0.6999 -0.0073 0.1176 -0.0407 0.0814 0.0242 0.7923 0.0431 

0.8230 0.0320 0.6999 -0.0100 0.1083 -0.0394 0.0857 0.0263 0.7998 0.0422 

0.8163 0.0320 0.6999 -0.0125 0.1003 -0.0383 0.0904 0.0285 0.8068 0.0413 

0.8088 0.0320 0.6999 -0.0149 0.0933 -0.0374 0.0957 0.0307 0.8131 0.0404 

0.8004 0.0320 0.6999 -0.0172 0.0874 -0.0365 0.1014 0.0330 0.8190 0.0396 

0.7912 0.0320 0.6977 -0.0176 0.0823 -0.0357 0.1077 0.0353 0.8244 0.0389 

0.7826 0.0320 0.6951 -0.0181 0.0779 -0.0349 0.1146 0.0376 0.8293 0.0382 

0.7746 0.0320 0.6921 -0.0187 0.0742 -0.0343 0.1221 0.0399 0.8339 0.0375 

0.7672 0.0320 0.6886 -0.0193 0.0709 -0.0337 0.1304 0.0422 0.8381 0.0369 

0.7603 0.0320 0.6845 -0.0201 0.0681 -0.0332 0.1395 0.0445 0.8420 0.0364 

0.7539 0.0320 0.6798 -0.0210 0.0658 -0.0328 0.1495 0.0467 0.8456 0.0358 

0.7480 0.0320 0.6744 -0.0220 0.0637 -0.0324 0.1604 0.0483 0.8489 0.0353 

0.7424 0.0320 0.6682 -0.0231 0.0619 -0.0320 0.1724 0.0496 0.8519 0.0348 

0.7373 0.0320 0.6609 -0.0245 0.0604 -0.0317 0.1855 0.0508 0.8547 0.0344 

0.7325 0.0320 0.6525 -0.0260 0.0591 -0.0315 0.1997 0.0521 0.8572 0.0339 

0.7281 0.0320 0.6428 -0.0278 0.0580 -0.0312 0.2152 0.0533 0.8596 0.0335 

0.7240 0.0320 0.6315 -0.0298 0.0567 -0.0310 0.2320 0.0546 0.8618 0.0332 

0.7201 0.0320 0.6184 -0.0321 0.0555 -0.0307 0.2503 0.0558 0.8638 0.0328 

0.7166 0.0320 0.6033 -0.0346 0.0543 -0.0303 0.2702 0.0570 0.8656 0.0325 

0.7133 0.0320 0.5858 -0.0373 0.0532 -0.0299 0.2919 0.0581 0.8673 0.0322 

0.7102 0.0320 0.7073 0.0320 0.5654 -0.0404 0.3155 0.0592 0.8689 0.0319 

0.8740 0.0309 0.7047 0.0320 0.5419 -0.0436 0.3412 0.0601 0.8703 0.0316 

0.8729 0.0310 0.7022 0.0320 0.5145 -0.0466 0.3691 0.0609 0.8717 0.0314 

0.8716 0.0311 0.6999 0.0320 0.4828 -0.0497 0.3995 0.0615 0.8729 0.0312 

0.8702 0.0311 0.6999 0.0297 0.4459 -0.0521 0.4326 0.0619 0.8740 0.0309 

0.8686 0.0312 0.6999 0.0273 0.4033 -0.0540 0.4686 0.0619 

0.8669 0.0313 0.6999 0.0246 0.3538 -0.0544 0.5017 0.0616 

NASA/TM—2002-211700 370
Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

0.0521 -0.0294 

0.0511 -0.0288 

0.0502 -0.0282 

0.0493 -0.0276 

0.0484 -0.0269 

0.0476 -0.0260 

0.0468 -0.0250 

0.0460 -0.0239 

0.0454 -0.0228 

0.0449 -0.0216 

0.0445 -0.0204 

0.0442 -0.0192 

0.0439 -0.0179 

0.0438 -0.0167 

0.0439 -0.0154 

0.0440 -0.0142 

0.0441 -0.0129 

0.0443 -0.0117 

0.0446 -0.0105 

0.0448 -0.0093 

0.0452 -0.0082 

0.0456 -0.0071 

0.0461 -0.0060 

0.0466 -0.0049 

0.0472 -0.0039 

0.0477 -0.0029 

0.0484 -0.0019 

0.0490 -0.0010 

 

NASA/TM—2002-211700 371
Table B-8c Three-element High Lift System - Flap Element Coordinates 

Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

1.1283 -0.1458 1.0331 -0.0800 0.8749 -0.0040 0.8715 0.0067 0.9222 0.0157 1.0712 -0.0831 

1.1280 -0.1455 1.0250 -0.0757 0.8745 -0.0033 0.8716 0.0077 0.9245 0.0148 1.0738 -0.0853 

1.1276 -0.1453 1.0162 -0.0712 0.8740 -0.0025 0.8717 0.0087 0.9269 0.0139 1.0763 -0.0875 

1.1272 -0.1451 1.0068 -0.0664 0.8736 -0.0017 0.8719 0.0096 0.9294 0.0130 1.0786 -0.0896 

1.1268 -0.1447 0.9978 -0.0621 0.8732 -0.0009 0.8721 0.0105 0.9319 0.0119 1.0809 -0.0917 

1.1264 -0.1444 0.9894 -0.0582 0.8728 0.0000 0.8724 0.0114 0.9345 0.0108 1.0831 -0.0937 

1.1260 -0.1440 0.9814 -0.0546 0.8725 0.0009 0.8727 0.0122 0.9372 0.0097 1.0852 -0.0956 

1.1255 -0.1436 0.9739 -0.0513 0.8722 0.0018 0.8731 0.0130 0.9399 0.0085 1.0873 -0.0974 

1.1250 -0.1432 0.9669 -0.0482 0.8719 0.0027 0.8735 0.0138 0.9428 0.0071 1.0892 -0.0992 

1.1245 -0.1427 0.9603 -0.0454 0.8717 0.0037 0.8740 0.0145 0.9456 0.0058 1.0911 -0.1009 

1.1239 -0.1422 0.9540 -0.0429 0.8716 0.0047 0.8745 0.0152 0.9486 0.0043 1.0929 -0.1026 

1.1232 -0.1417 0.9481 -0.0405 0.8715 0.0058 0.8751 0.0159 0.9516 0.0028 1.0946 -0.1043 

1.1226 -0.1411 0.9426 -0.0383 0.8757 0.0166 0.9547 0.0011 1.0962 -0.1058 

1.1218 -0.1405 0.9375 -0.0362 0.8764 0.0172 0.9579 -0.0006 1.0978 -0.1074 

1.1211 -0.1398 0.9326 -0.0344 0.8771 0.0179 0.9612 -0.0024 1.0993 -0.1088 

1.1202 -0.1391 0.9280 -0.0326 0.8779 0.0185 0.9646 -0.0042 1.1008 -0.1103 

1.1193 -0.1383 0.9237 -0.0310 0.8788 0.0191 0.9680 -0.0062 1.1022 -0.1116 

1.1183 -0.1375 0.9197 -0.0295 0.8797 0.0196 0.9716 -0.0083 1.1035 -0.1130 

1.1173 -0.1366 0.9159 -0.0281 0.8807 0.0201 0.9752 -0.0105 1.1048 -0.1142 

1.1161 -0.1356 0.9124 -0.0268 0.8818 0.0205 0.9789 -0.0128 1.1061 -0.1155 

1.1149 -0.1346 0.9090 -0.0256 0.8829 0.0209 0.9828 -0.0151 1.1073 -0.1167 

1.1136 -0.1335 0.9059 -0.0245 0.8840 0.0213 0.9867 -0.0177 1.1084 -0.1178 

1.1121 -0.1324 0.9030 -0.0234 0.8853 0.0215 0.9907 -0.0203 1.1095 -0.1190 

1.1106 -0.1312 0.9002 -0.0224 0.8865 0.0218 0.9948 -0.0230 1.1106 -0.1200 

1.1089 -0.1298 0.8977 -0.0214 0.8879 0.0219 0.9990 -0.0259 1.1117 -0.1211 

1.1071 -0.1284 0.8953 -0.0204 0.8892 0.0220 1.0034 -0.0289 1.1127 -0.1221 

1.1051 -0.1269 0.8931 -0.0195 0.8906 0.0221 1.0078 -0.0321 1.1136 -0.1230 

1.1030 -0.1253 0.8910 -0.0185 0.8921 0.0221 1.0123 -0.0354 1.1145 -0.1240 

1.1007 -0.1236 0.8891 -0.0175 0.8936 0.0221 1.0169 -0.0389 1.1154 -0.1248 

1.0983 -0.1218 0.8874 -0.0165 0.8952 0.0220 1.0217 -0.0425 1.1163 -0.1257 

1.0956 -0.1198 0.8859 -0.0155 0.8968 0.0219 1.0262 -0.0460 1.1171 -0.1265 

1.0927 -0.1177 0.8844 -0.0145 0.8984 0.0217 1.0306 -0.0495 1.1179 -0.1273 

1.0896 -0.1155 0.8831 -0.0135 0.9001 0.0215 1.0348 -0.0528 1.1187 -0.1281 

1.0863 -0.1131 0.8820 -0.0125 0.9019 0.0212 1.0388 -0.0560 1.1194 -0.1288 

1.0827 -0.1105 0.8809 -0.0115 0.9037 0.0209 1.0426 -0.0591 1.1201 -0.1296 

1.0788 -0.1078 0.8800 -0.0105 0.9055 0.0205 1.0463 -0.0622 1.1208 -0.1302 

1.0745 -0.1049 0.8791 -0.0096 0.9074 0.0201 1.0499 -0.0651 1.1215 -0.1309 

1.0700 -0.1019 0.8783 -0.0087 0.9093 0.0196 1.0533 -0.0679 1.1221 -0.1315 

1.0650 -0.0987 0.8776 -0.0079 0.9113 0.0191 1.0566 -0.0706 1.1227 -0.1322 

1.0596 -0.0953 0.8770 -0.0070 0.9134 0.0185 1.0598 -0.0733 1.1233 -0.1328 

1.0537 -0.0917 0.8764 -0.0062 0.9155 0.0179 1.0628 -0.0759 1.1239 -0.1333 

1.0474 -0.0880 0.8759 -0.0055 0.9177 0.0172 1.0657 -0.0783 1.1244 -0.1339 

1.0405 -0.0841 0.8754 -0.0048 0.9199 0.0165 1.0685 -0.0807 1.1250 -0.1344 

NASA/TM—2002-211700 372
Lower Surface Upper Surface 

x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c x/c y/c 

 1.1255 -0.1349 

1.1260 -0.1354 

1.1265 -0.1359 

1.1269 -0.1363 

1.1274 -0.1368 

1.1278 -0.1372 

1.1282 -0.1376 

1.1286 -0.1380 

1.1290 -0.1384 

1.1293 -0.1388 

1.1297 -0.1391 

1.1300 -0.1395 

1.1303 -0.1398 

1.1306 -0.1401 

1.1309 -0.1405 

 

NASA/TM—2002-211700 373

Appendix C: Derivation of equation (5-3) – reflectivity 

curve error analysis 

C.1 Derivation of equation (5-3) 

Consider the system of linear differential equations 

jai Sdx

di

+−=− 

 iaj Sdx

dj +−= (C-1) 

Where 

S

KS

a

+ = with boundary conditions, 

x = 0, r = Rg (C-2) 

x = X, r = R

Letting i

j r = and differentiating with respect to x, 

2

i

dx

jdi

dx

idj

dx

dr −

= (C-3 ) 

Dividing both sides of Equation (C-3) by S, 

2

i

Sdx

jdi

Sdx

idj

Sdx

dr −

=

Using Equations (C-1) 

NASA/TM—2002-211700 375
 

 1 r 2ar

i

aij i j aij 

i

i( aj i ) j( ai j )

Sdx

dr

2

2

2 2

2

= + −

− + + − =

− + + − + =

 (C-4) 

 

Integrating (B-4), 

∫ ∫ − + =

X

0

R

Rg

2 r 2ar 1

dr

s dx

From Reference 27, page 296, integral 110, 

R

Rg

2

1

2 4(1 a )

2r 2a tanh

4(1 a )

2 S[X - 0]

















− −

−

− −

− = −

Let b a 1 2 = − (b a 1,a b 1) 2 2 2 2 = − = +

b

R a

tanh

b

R a tanh

b

-1 SX

b

r a tanh

b

1 SX

1 1 g

R

Rg

1

− − − =

− − =

− −

−

From Reference 27, page 233, 





 





−

− − = − − −

1 xy

x y tanh x tanh y tanh 1 1 1

Using the above result 











































 − 



 



 − −

− − −

− = −

b

R a

b

R a 1

b

R a

b

R a

tanh

b

1 SX

g

g

1

NASA/TM—2002-211700 376
[ ]

b (R a)(R a)

b(R R )

b (R a)(R a) b

(R R ) b

g

2

g

2

g

2

g

− − −

− = −

− − −

− tanh(bSX) = −

tanh(bSX) b (RR R R a a ) b(R R ) g

2

g a g

2 − − − + = − −

b (RR R R a a ) b(R R ) g

2

g a g

2 tanh(bSX) − + + − = − −

tanh(bSX)(a 1 RR Ra R a a ) b(R R ) g

2

g g

2 − − + + − = − −

g g bR bRg tanh(bSX)(R a + R(a − R ) −1) = − +

tanh(bSX)(R a 1) bR bR R(a R )tanh(bSX ) g − − g = − − − g

(b (a R )tanh(bSX ))

bR tanh(bSX )(R a 1) R

g

g g

− + −

− + − =

(b (a R )tanh(bSX ))

R ( b atanh(bSX ) tanh(bSX ) R

g

g

− + −

− + − =

dividing by tanh(bSX), 

(a bcoth(bSX ) R )

R ( b coth(bSX ) a) 1

R

g

g

− + −

− + − =

g

g

a b coth(bSX ) R

1 R (a b coth(bSX )) R

+ −

− − =

C. 2 Reflectivity Curve error analysis 

Let K = ac where c is the dye concentration and a is a constant. Using the 

above equation for K, 

S

ac S

a

+ = (C-5) 

SX

ac(ac 2S) b + =

Let 

D

N R = where, 

N 1 R (a bcoth(bSX )) = − g − (C-6) 

Rg D = a + b coth(bSX ) −

NASA/TM—2002-211700 377
Differentiating R with respect to c, 

F(c ) dc

dD

D

N

dc

dN

D

1

D

dc

dD N

dc

dN D

dc

dR

2 2 = − =

−

= (C-7) 

where, 

coth(bSX ) dc

d b

dc

db coth(bSX ) dcda 0 R

dc

dN = − g − − 

coth(bSX ) 0

dc

d b

dc

db coth(bSX ) dcda

dc

dD = + + −

S

a

dc

da =

S ac(ac 2S)

a(ac S)

2 ac(ac 2S)

a(ac 2S) a c

S

1

dc

db 2

+

+ = ++ + =

dc

db

sinh(bSX )

SX

csc h (bSX ) dc

d(bSX ) coth(bSX ) dcd 2 − = − =

Multiplying both sides of Equation (C-7) 

F(c ) R

c

R

c

dc

dR =

Rearranging 

c

dc F(c ) Rc

R

dR =

where dc/c is the relative error in dye concentration due to an error in the value of 

reflectivity. 

Solving for dc/c and normalizing the reflectance with respect to ε , the 

reflectance value corresponding to c = 0, (zero dye concentration) yields 

R

dR

F(c)

1

c

R

c

dc

ε = (C-8) 

Where, 

2 Rg

1

− ε =

NASA/TM—2002-211700 378
Date : August 1, 1997

PBAR : 14.40 psiaDYE CONCENTRATION : 0.0002 grams/ccPSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. Air TAS P∞ PRESS D. C. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. TEMP. (MPH) (PSIA) TOTAL grams/cc % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

( F) (PSIA)

1 wir0001 44.5 176 13.836 14.367 0.002 59.33 0.294118 20 68 20 68 30 19:13 20 IRT air off, r11all.pmi2 wir0002 43.8 176 13.836 14.367 0.002 59.7 0.294118 20 68 20 68 30 19:16 20 IRT air off, r11all.pmi (redo wir0001)3 wir0003 41.4 175 13.836 14.367 0.002 53.8 0.294118 20 68 20 68 30 19:19 20 IRT air off, r11all.pmi4 wir0004 43.9 176 13.836 14.367 0.002 64.94 0.294118 20 68 20 68 30 19:21 20 IRT air on (80 lbs pressure)5 wir0005 45.1 176 13.836 14.367 0.002 61.23 0.294118 20 68 20 68 30 19:23 20 IRT air on (80 lbs pressure)6 wir0006 44.2 176 13.836 14.367 0.002 54.08 0.634921 40 63 40 63 30 19:37 12 IRT air on (80 lbs pressure)7 wir0007 43 175 13.836 14.367 0.002 57.67 0.634921 40 63 40 63 30 19:40 12 IRT air on (80 lbs pressure)8 wir0008 44.2 176 13.836 14.367 0.002 54.91 0.634921 40 63 40 63 30 19:43 12 IRT air off9 wir0009 42.1 176 13.836 14.367 0.002 61.5 0.634921 40 63 40 63 30 19:46 12 IRT air off

10 wir0010 45.1 176 13.836 14.367 0.002 64.36 0.151515 5 33 5 33 30 19:57 120 IRT air off11 wir0011 44.4 176 13.836 14.367 0.002 55.23 0.151515 5 33 5 33 30 19:58 120 IRT air off12 wir0012 39.6 176 13.836 14.367 0.002 67.26 0.151515 5 33 5 33 30 20:02 120 IRT air on (80 lbs pressure)13 wir0013 43.5 176 13.836 14.367 0.002 61.72 0.151515 5 33 5 33 30 20:10 120 IRT air on (80 lbs pressure)14 wir0014 43.3 175 13.836 14.367 0.002 60.35 0.151515 5 33 5 33 4 20:15 120 IRT air on (80 lbs pressure)15 wir0015 40.4 176 13.836 14.367 0.002 63 0.151515 5 33 5 33 4 20:42 120 IRT air on (80 lbs pressure), Penetration Test16 wir0016 44.4 176 13.836 14.367 0.002 66.6 0.151515 5 33 5 33 4 20:57 120 IRT air off17 wir0017 47.3 176 13.836 14.367 0.002 82.06 0.151515 5 33 5 33 5 21:47 120 IRT air on (80 lbs pressure)18 wir0018 39.2 176 13.836 14.367 0.002 84.33 0.294118 20 68 20 68 6 22:02 20 IRT air on (80 lbs pressure)19 wir0019 41.8 175 13.836 14.367 0.002 68.4 0.294118 20 68 20 68 4 22:13 20 IRT air on (80 lbs pressure)20 wir0020 42.7 176 13.836 14.367 0.002 68.51 0.634921 40 63 40 63 4 22:23 12 IRT air on (80 lbs pressure)21 wir0021 46.8 176 13.836 14.367 0.002 72.17 0.151515 5 33 5 33 4 22:46 120 IRT air on (80 lbs pressure)

Appendix D: Run Log for 1997 Impingement Tests

NASA/TM—2002-211700 379
Date : August 4, 1997

PBAR : 14.30 psiaDYE CONCENTRATION : 0.0002 grams/ccPSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. Air TAS P∞ PRESS D. C. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. TEMP. (MPH) (PSIA) TOTAL grams/cc % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME IRT air set to 80 lbs unless otherwise specified

(oF) (PSIA) (oF)

1 wir0022 44.5 176 13.76 14.28 0.002 58.5 0.151515 5 33 4 39 4 20:36 120 IRT air on; all nozzles on; blotter squares used2 wir0023 48.6 176 13.76 14.291 0.002 61.3 0.151515 5 33 4 39 4 20:56 120 IRT air on; all nozzles on; blotter strips used3 wir0024 43.9 176 13.77 14.307 0.002 71.6 0.151515 5 33 4 39 4 21:17 120 IRT air on; all nozzles on; blotter squares used4 wir0025 41.4 176 13.77 14.307 0.002 70.6 0.294118 20 68 22 74 4 21:46 20 IRT air on; all nozzles on except 115 wir0026 43.9 176 13.77 14.307 0.002 64 0.634921 40 63 43.5 67 4 22:04 12 IRT air on; all nozzles on6 wir0027 39.1 176 13.77 14.307 0.002 73.05 0.634921 40 63 44 67 6 22:13 12 Repeat of wir0026; not enough dye on blotters.7 wir0028 41 175 13.77 14.3 0.002 64.3 0.634921 40 63 44 67 12 22:25 12 IRT air on; all nozzles on except 11;12 seconds to accumulate dye8 wir0029 44.7 176 13.77 14.3 0.002 71.56 0.634921 40 63 44 67 10 22:36 12 IRT air on; all nozzles on; using thin collector strips; strip 33V left on9 wir0030 42.5 175 13.77 14.3 0.002 65.89 0.294118 20 68 22 74 4 22:51 20 IRT air on; all nozzles on; using thin collector strips

10 wir0031 42.7 177 13.77 14.3 0.002 62.01 0.151515 5 33 4 39 4 23:06 120 IRT air on; all nozzles on; using thin collector strips

NASA/TM—2002-211700 380
Date : August 5, 1997 Note: 

PBAR : 14.35 psia 1. MVD measurement methodology:DYE CONCENTRATION : 0.0002 grams/cc a) Optical Array Prob (OAP)PSYCHROMETER READINGS : 12345 oF DB b)Forward Scrattering Spectrometer Probe (FSSP)

: 12345 oF DB 2. 47 MVD is the largest droplet size for FSSP system

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. Air TAS P∞ PRESS D. C. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. TEMP. (MPH) (PSIA) TOTAL grams/cc % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (IRT air pressure is set to 80 lbs)

1 wir0032 38.6 176 13.82 14.352 0.002 60.42 0.634921 40 63 43.5 67 120 18:28 12 Nozzle #11 off, IRT air off, FSSP -- average MVD 122 wir0033 43.1 177 13.838 14.36 0.002 53.56 0.634921 40 63 43.5 67 120 18:34 12 Nozzle #11 off, IRT air on, FSSP -- average MVD 11.93 wir0034 43.6 176 13.819 14.362 0.002 53.91 0.634921 40 63 44 67 120 18:38 12 All Nozzles on, IRT air on, FSSP -- average MVD 11.74 wir0035 41.8 176 13.793 14.353 0.002 52.25 0.634921 40 63 44 67 120 18:43 12 All Nozzles on, IRT air off, FSSP -- average MVD 11.85 wir0036 42.3 176 13.813 14.348 0.002 48.85 0.294118 20 68 22 74 120 18:50 20 Nozzle #11 off, IRT air off, FSSP -- average MVD 21.16 wir0037 43.2 176 13.838 14.36 0.002 59.95 0.294118 20 68 22 74 120 18:57 20 Nozzle #11 off, IRT air on, FSSP -- average MVD 21.17 wir0038 38.5 175 13.838 14.362 0.002 57.3 0.151515 5 33 4 39 120 19:06 120 All Nozzles on, IRT air on, FSSP -- average MVD (not available for FSSP system)8 wir0039 44.2 176 13.808 14.353 0.002 54.96 0.151515 5 33 4 39 120 19:13 120 All Nozzles on, IRT air off, FSSP -- average MVD (not available for FSSP system) 9 wir0040 44.1 176 13.818 14.356 0.002 57.89 0.294118 20 68 22 74 120 19:19 20 Nozzle #11 off, IRT air off, FSSP -- average MVD 20.8

10 wir0041 43.9 176 13.823 14.361 0.002 61.08 0.294118 20 68 22 74 120 19:50 20 Nozzle #11 off, IRT air off, OAP 11 wir0042 43.9 176 13.823 14.361 0.002 61.08 0.294118 20 68 22 74 120 19:55 20 Nozzle #11 off, IRT air off, OAP (repeat Runt #41)12 wir0043 42.7 174 13.835 14.364 0.002 57.84 0.294118 20 68 22 74 120 20:02 20 Nozzle #11 off, IRT air on, OAP13 wir0044 43.9 174 13.832 14.364 0.002 46.26 0.151515 5 33 4 39 120 20:12 120 All Nozzles on, IRT air on, OAP -- average MVD 10614 wir0045 40.3 175 13.819 14.354 0.002 58.28 0.151515 5 33 4 39 120 20:18 120 All Nozzles on, IRT air off, OAP -- average MVD 11115 wir0056** 39.9 176 13.815 14.366 0.002 61.40 0.634921 40 63 44 67 120 22:06 12 Nozzle #11 off, IRT air off, LWC test -- average LWC = 0.05 grams/m3 (0.04 -- 0.06)16 wir0057 40.7 177 13.819 14.364 0.002 61.84 0.634921 40 63 44 67 120 22:13 12 All Nozzles on, IRT air off, LWC test -- average LWC = 0.045 grams/m3 (0.04 -- 0.05)17 wir0058 43.6 176 13.843 14.368 0.002 57.5 0.634921 40 63 44 67 120 22:18 12 All Nozzles on, IRT air on, LWC test -- average LWC = (fail to record the reading)18 wir0059 41.5 176 13.828 14.371 0.002 54.23 0.634921 40 63 44 67 120 22:24 12 Repeat Run #58, LWC test -- average LWC = 0.025 grams/m3 (0.02 -- 0.03)19 wir0060 44.4 176 13.831 14.371 0.002 51.81 0.634921 40 63 44 67 120 22:29 12 Nozzle #11 off, IRT air on, LWC test -- average LWC = 0.015 grams/m3 (0.01 -- 0.02)20 wir0061 43.9 174 13.826 14.369 0.002 48.10 0.294118 20 68 22 74 120 22:34 20 Nozzle #11 off, IRT air on, LWC test -- average LWC = 0.095 grams/m3 (0.08 -- 0.011)21 wir0062 45.3 175 13.823 14.362 0.002 49.00 0.294118 20 68 22 74 120 22:41 20 Nozzle #11 off, IRT air off, LWC test -- average LWC = 0.14 grams/m3 (0.09 -- 0.18)22 wir0063 43.6 175 13.821 14.36 0.002 50.73 0.151515 5 33 4 39 120 22:49 120 All Nozzles on, IRT air off, LWC test -- average LWC = 0.20 grams/m3 (0.16 -- 0.26)23 wir0064 43.2 176 13.89 14.368 0.002 50.44 0.151515 5 33 4 39 120 22:53 120 All Nozzles on, IRT air on, LWC test -- average LWC = 0.16 grams/m3 (0.14 -- 0.18)24 wir0065 44.8 176 13.826 14.364 0.002 47.4 #VALUE! 2.6 40.28 120 23:00 high All Nozzles on, IRT air on, LWC test -- average LWC = 0.18 grams/m3 (0.14-0.21)25 wir0066 43.9 177 13.839 14.367 0.002 47.63 #VALUE! 2 40 120 23:05 higher All Nozzles on, IRT air on, LWC test -- average LWC = 0.16 grams/m3 (0.13-0.19)

** There are 10 trial runs (#46 - #55) which are not recorded in this table, but they can be found in the daily back up disk (Zip disk -- NASA #2)

NASA/TM—2002-211700 381
Note : 

1. Test Model : MS 317

Date : August 6, 1997 2. Verigood 100 New and Whatman 3MM papers strips are used.PBAR : 14.40 psia 3. IRT air remained on at 20 lbs to prevent the water leaking DYE CONCENTRATION : 0.0002 grams/cc from some IRT's nozzles when the tunnel was down.PSYCHROMETER READINGS : 4. MS 317 pressure data was taken by IRT's system

: (record #2176 -- #2193, see Colin's notes in Aug. 7's folder)

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION PRESSURE INDICATOR TANK TIME REMARKS

 PRESSURE ** IRT 80 lbs air

RUN Run I.D. Air TAS P∞ PRESS D. C. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. TEMP. (MPH) (PSIA) TOTAL grams/cc % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME IRT air set to 80 lbs unless otherwise specified

(oF) (PSIA) 

1 wir0067 41.6 177 13.816 14.362 0.002 57.25 0.292517 22.36 76.44 22 74 4 18:36 22 Nozzle #11 off, IRT air on, flow rate 0.31 galons/min (darker than the cllector)

2 wir0068 41.7 176 13.868 14.408 0.002 48 0.287484 22.05 76.7 22 74 4 20:42 22 Nozzle #11 off, IRT air on, 3 wir0069 43 176 13.83 14.401 0.002 54.71 0.378449 28.8 76.1 22 74 4 21:03 22 Nozzle #11 off, IRT air on4 wir0070 45.6 176 13.86 14.409 0.002 57.42 0.293034 22.42 76.51 22 74 4 21:21 22 Nozzle #11 off, IRT air on5 wir0071 40.5 176 13.861 14.405 0.002 52.2 0.28987 21.92 75.62 22 74 4 21:34 22 Nozzle #11 off, IRT air off6 wir0072 40.5 176 13.868 14.415 0.002 50.58 0.103832 4.2 40.45 4 39 4 22:21 92 All Nozzles on, IRT air on (see Note #3)7 wir0073 42.7 176 13.916 14.429 0.002 55.7 0.104223 4.22 40.49 4 39 4 22:49 92 All Nozzles on, IRT air on8 wir0074 40.6 13.88 14.415 0.002 44.56 0.102666 4.12 40.13 4 39 4 23:00 92 All Nozzles on, IRT air on

NASA/TM—2002-211700 382
Date : August 7, 1997 Note:

PBAR : 13.90 psia 1. WIR0075 -- WIR0084 are the flow visualization versusDYE CONCENTRATION : 0.0002 & 0.0003 grams/cc AOA Test, image files were savedPSYCHROMETER READINGS : 2. Concentration was changed from 0.0002 grams/cc to

: 0.0003 grams/cc at 20:20 - 21:20 (from WIR0099)

 3. Both Verigood 100 New and Whatman 3MM paper were used

4. Test Model: MS317

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION PRESSURE INDICATOR TANK TIME REMARKS

 PRESSURE

RUN Run I.D. Air TAS P∞ PRESS D. C. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. TEMP. (MPH) (PSIA) TOTAL grams/cc % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) (PSIA) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0075 46.9 176 13.894 14.436 0.002 54.75 0.291159 22 75.56 22 74 30 16:54 22 Nozzle #11 off, IRT air on, AOA = -4.0 deg., filename: am4.pmi2 wir0076 43.7 177 13.902 14.435 0.002 53.44 0.294821 22.2 75.3 22 74 30 17:04 22 Nozzle #11 off, IRT air on, AOA = 0 deg., file name: a0.pmi3 wir0077 46.4 176 13.886 14.436 0.002 60.08 0.294651 22.09 74.97 22 74 30 17:07 22 Nozzle #11 off, IRT air on, AOA = 4.0 deg., filename: ap4.pmi4 wir0078 38.6 176 13.891 14.437 0.002 63.79 0.296791 22.2 74.8 22 74 30 17:10 22 Nozzle #11 off, IRT air on, AOA = 8.0 deg., filename: ap8.pmi5 wir0079 41.8 176 13.896 14.432 0.002 63.79 0.294094 21.96 74.67 22 74 30 17:13 22 Nozzle #11 off, IRT air on, AOA = 10.0 deg. filename: ap10.pmi6 wir0080 46.0 175 13.894 14.435 0.002 57.76 0.292279 21.88 74.86 22 74 30 17:16 22 Only Nozzle #12, #10, and #2 are on, IRT air on, AOA = 10.0 deg. filename: R80.pmi7 wir0081 46.0 175 13.894 14.435 0.002 57.76 0.292279 21.88 74.86 22 74 30 17:21 22 repeat WIR0080, filename: R81.pmi8 wir0082 42.8 177 13.881 14.43 0.002 58.45 0.290495 21.7 74.7 22 74 30 17:24 22 Only Nozzle #1, #4, and #10 are on, IRT air on, AOA = 10.0 deg, filename: R82.pmi9 wir0083 44.8 174 13.912 14.433 0.002 50.78 0.290551 21.71 74.72 22 74 30 17:28 22 Only Nozzle #1, #4, and #10 are on, IRT air on, AOA = 0.0 deg, filename: R83.pmi

10 wir0084 39.4 176 13.886 14.429 0.002 60.16 0.292464 21.85 74.71 22 74 30 17:30 22 Only Nozzle #12, #10, and #2 are on, IRT air on, AOA = 0.0 deg. filename: R84.pmi11 wir0085 39.4 176 13.894 14.429 0.002 53.22 0.627197 43.17 68.83 44 67 10 17:46 12 Nozzle #11 off, IRT air on, AOA = 0.0 deg.12 wir0086 40.6 176 13.89 14.429 0.002 59.79 0.635327 43.45 68.39 44 67 10 17:59 12 Nozzle #11 off, IRT air on, AOA = 0.0 deg.13 wir0087 44.9 176 13.887 14.425 0.002 52.49 0.625942 43.19 69 44 67 15 18:08 12 Nozzle #11 off, IRT air on, AOA = 0.0 deg.14 wir0088 40.8 175 13.885 14.43 0.002 65.79 0.642433 43.3 67.4 44 67 20 18:18 12 Nozzle #11 off, IRT air on, AOA = 0.0 deg.15 wir0089 42.5 174 13.895 14.427 0.002 55.37 0.351032 23.8 67.8 44 67 20 18:32 12 Nozzle #11 off, IRT air on, AOA = 8.0 deg.16 wir0090 43.2 177 13.89 14.127 0.002 52.81 0.640343 43.3 67.62 44 67 20 18:42 12 Nozzle #11 off, IRT air on, AOA = 8.0 deg.17 wir0091 44.1 175 13.888 14.426 0.002 50.103 0.632051 43.7 69.14 44 67 20 18:51 12 Nozzle #11 off, IRT air on, AOA = 8.0 deg.18 wir0092 46 175 13.894 14.427 0.002 49.46 0.286013 21.88 76.5 22 74 4 19:03 22 Nozzle #11 off, IRT air on, AOA = 8.0 deg.19 wir0093 39.8 176 13.889 14.43 0.002 66.8 0.291503 22.3 76.5 22 74 4 19:17 22 Nozzle #11 off, IRT air on, AOA = 8.0 deg.20 wir0094 43.1 174 13.89 14.427 0.002 56 0.294654 22.6 76.7 22 74 8 19:24 22 Nozzle #11 off, IRT air on, AOA = 8.0 deg.21 wir0095 41.9 176 13.897 14.429 0.002 61.108 0.290743 22.3 76.7 22 74 8 19:33 22 Nozzle #11 off, IRT air on, AOA = 8.0 deg.22 wir0096 41 176 13.881 14.427 0.002 65.01 0.109696 4.48 40.84 4 39 3 19:50 92 All Nozzles on, IRT air on, AOA = 8.0 deg.23 wir0097 35.8 175 13.887 14.43 0.002 77.2 0.108115 4.41 40.79 4 39 4 20:00 92 All Nozzles on, IRT air on, AOA = 8.0 deg.24 wir0098 39.5 175 13.885 14.424 0.002 59.94 0.107711 4.4 40.85 4 39 3 20:10 92 All Nozzles on, IRT air on, AOA = 8.0 deg.25 wir0099 46.3 175 13.891 14.43 0.003 56.05 0.104028 4.21 40.47 4 39 3 22:01 92 All Nozzles on, IRT air on, AOA = 8.0 deg. (concentration 0.0003 from this run)26 wir0100 48.9 176 13.904 14.436 0.003 59.01 0.104294 4.25 40.75 4 39 3 22:11 92 All Nozzles on, IRT air on, AOA = 8.0 deg.27 wir0101 47.8 175 13.895 14.434 0.003 56.05 0.288626 22.23 77.02 22 74 4 22:22 22 Nozzle #11 off, IRT air on, AOA = 8.0 deg.28 wir0102 47.1 174 13.901 14.435 0.003 48 0.290062 22.3 76.88 22 74 8 22:29 22 Nozzle #11 off, IRT air on, AOA = 8.0 deg.29 wir0103 48.3 176 13.903 14.436 0.003 49.37 0.633577 43.4 68.5 44 67 15 22:39 12 Nozzle #11 off, IRT air on, AOA = 8.0 deg.30 wir0104 50.6 177 13.905 14.435 0.003 53.71 0.634111 43.5 68.6 44 67 20 22:46 12 Nozzle #11 off, IRT air on, AOA = 8.0 deg.31 wir0105 49.8 174 13.91 14.436 0.003 49.8 0.633382 43.45 68.6 44 67 20 22:57 12 Nozzle #11 off, IRT air on, AOA = 0.0 deg.

NASA/TM—2002-211700 383
Date : August 8, 1997

PBAR : 14.40 psiaDYE CONCENTRATION : 0.0003 grams/ccPSYCHROMETER READINGS :

: Note:

 1. Test Model: MS 317  2. Continuation from August 7, 1997

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION PRESSURE READING TANK TIME REMARKS

 PRESSURE

RUN Run I.D. Air TAS P∞ PRESS D. C. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. TEMP. (MPH) (PSIA) TOTAL grams/cc % PWATER Display Display Gauge Gauge (SEC) TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) (PSIA) (psig) (psig) (psig) (psig) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0106 42.2 177 13.879 14.403 0.0003 58.62 0.62789 43.45 69.2 44 67 60 17:39 12 Nozzle #11 off, IRT air on, AOA = 0.0 deg.2 wir0107 37 174 13.853 14.4 0.0003 70.53 0.629443 43.74 69.49 44 67 50 17:48 12 Nozzle #11 off, IRT air on, AOA = 0.0 deg.3 wir0108 44.2 176 13.871 14.396 0.0003 58.08 0.61516 42.2 68.6 44 67 40 17:56 12 Nozzle #11 off, IRT air on, AOA = 0.0 deg.4 wir0109 47 174 13.879 14.338 0.0003 54.71 0.634182 43.86 69.16 44 67 30 18:04 12 Nozzle #11 off, IRT air on, AOA = 0.0 deg.5 wir0110 45.9 176 13.866 14.395 0.0003 54.92 0.292375 22.7 77.64 22 74 4 18:16 22 Nozzle #11 off, IRT air on, AOA = 0.0 deg.6 wir0111 47.8 176 13.864 14.4 0.0003 51.27 0.302477 23.2 76.7 22 74 6 18:25 22 Nozzle #11 off, IRT air on, AOA = 0.0 deg.7 wir0112 45.7 174 13.875 14.4 0.0003 53.27 0.300952 23.08 76.69 22 74 8 18:33 22 Nozzle #11 off, IRT air on, AOA = 0.0 deg.8 wir0113 47.6 176 13.865 14.397 0.0003 49.51 0.304639 23.18 76.09 22 74 6 18:40 22 Nozzle #11 off, IRT air on, AOA = 0.0 deg.9 wir0114 47.4 176 13.86 14.398 0.0003 50.02 0.308594 23.7 76.8 22 74 6 18:49 22 Nozzle #11 off, IRT air on, AOA = 0.0 deg.

10 wir0115 46.7 176 13.859 14.402 0.0003 50 0.309694 23.8 76.85 22 74 6 18:56 22 Nozzle #11 off, IRT air on, AOA = 0.0 deg.11 wir0116 47.5 176 13.866 14.398 0.0003 48 0.309292 23.8 76.95 22 74 6 19:02 22 Nozzle #11 off, IRT air on, AOA = 8.0 deg.12 wir0117 47.1 176 13.868 14.396 0.0003 47.396 0.295573 22.7 76.8 22 74 6 19:09 22 Nozzle #11 off, IRT air on, AOA = 8.0 deg.13 wir0118 47.3 175 13.86 14.395 0.0003 43.8 0.296489 22.8 76.9 22 74 6 19:17 22 Nozzle #11 off, IRT air on, AOA = 8.0 deg.14 wir0119 44.6 175 13.862 14.392 0.0003 50 0.296345 22.7 76.6 22 74 6 19:24 22 Nozzle #11 off, IRT air on, AOA = 8.0 deg.15 wir0120 40.5 175 13.857 14.399 0.0003 58.394 0.643068 43.6 67.8 44 67 30 19:56 12 Nozzle #11 off, IRT air on, AOA = 8.0 deg.16 wir0121 42.9 175 13.855 14.397 0.0003 51.56 0.645066 43.8 67.9 44 67 30 20:03 12 Nozzle #11 off, IRT air on, AOA = 8.0 deg.17 wir0122 47.2 175 13.871 14.395 0.0003 54.59 0.636989 43.5 68.29 44 67 30 20:11 12 Nozzle #11 off, IRT air on, AOA = 8.0 deg.18 wir0123 43.4 177 13.853 14.393 0.0003 55.44 0.642647 43.7 68 44 67 30 20:19 12 Nozzle #11 off, IRT air on, AOA = 0.0 deg.19 wir0124 45.5 176 13.849 14.392 0.0003 49.8 0.638734 43.6 68.26 44 67 30 20:26 12 Nozzle #11 off, IRT air on, AOA = 0.0 deg.20 wir0125 45.8 177 13.862 14.396 0.0003 48 0.109877 4.45 40.5 4 39 3 20:41 92 All Nozzles on, IRT air on, AOA = 0.0 deg.21 wir0126 47.5 177 13.852 14.393 0.0003 50.07 0.108374 4.4 40.6 4 39 3 20:52 92 All Nozzles on, IRT air on, AOA = 0.0 deg.22 wir0127 47.7 175 13.865 14.389 0.0003 50.51 0.112887 4.59 40.66 4 39 3 20:59 92 All Nozzles on, IRT air on, AOA = 0.0 deg.23 wir0128 47.2 176 13.86 14.392 0.0003 40.16 0.108374 4.4 40.6 4 39 3 21:09 92 All Nozzles on, IRT air on, AOA = 8.0 deg.24 wir0129 46.9 176 13.86 13.39 0.0003 41.9 0.107658 4.4 40.87 4 39 3 21:17 92 All Nozzles on, IRT air on, AOA = 8.0 deg.25 wir0130 47.5 175 13.859 14.392 0.0003 43.7 0.108241 4.4 40.65 4 39 3 21:25 92 All Nozzles on, IRT air on, AOA = 8.0 deg.

NASA/TM—2002-211700 384
Date : August 11, 1997 Note:

PBAR : 14.40 psia 1. WIR0131 -- WIR0142 are the flow visulization tests:DYE CONCENTRATION : 0.0003 grams/cc a) with empty test section (Run #131 -- #136)PSYCHROMETER READINGS : b) with collector mechanism in test section (Run #137 ~~ #142)

: 2. Image exposure time is 10 seconds.

 3. Laser system power setting is 6 Watts 4. Test model : Collector Mechanism

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION PRESSURE READING TANK TIME REMARKS

Disk Digital Display Reading PRESSURE

RUN Run I.D. Air TAS A.O.A P∞ PRESS Humidity PAIR PAIR PWATER PAIR PWATER SPRAY CLOCK MVD

NO. TEMP. (MPH) (deg.) (PSIA) TOTAL % PWATER Display Display Gauge Gauge (SEC) TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) (PSIA) (psig) (psig) (psig) (psig) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0131 48.4 174 ** 13.87 14.411 N/A 0.112883 4.6 40.75 4 39 30 17:20 92 All Nozzles on, IRT air on, Empty Tunnel, filename: r131.pmi2 wir0132 47.1 176 ** 13.87 14.412 N/A 0.107527 4.4 40.92 4 39 30 17:21 92 Repeat WIR0131, filename: r132.pmi3 wir0133 46.6 176 ** 13.874 14.413 N/A 0.645185 43.55 67.5 44 67 30 17:30 12 Nozzle #11 off, IRT air on, Empty Tunnel, filename: r133.pmi4 wir0134 47.5 175 ** 13.868 14.411 N/A 0.643068 43.6 67.8 44 67 30 17:33 12 Repeat WIR0133, filename: r134.pmi5 wir0135 46.3 176 ** 13.871 14.411 N/A 0.296345 22.7 76.6 22 74 30 17:39 22 Nozzle #11 off, IRT air on, Empty Tunnle, filename: r135.pmi6 wir0136 45.2 176 ** 13.875 14.411 N/A 0.294271 22.6 76.8 22 74 30 17:42 22 Repeat WIR0135, filename: r136.pmi7 wir0137 48.0 177 0.0 13.897 14.406 N/A 0.293734 22.5 76.6 22 74 30 18:42 22 Nozzle #11 off, IRT air on, Collector Mechansim in Test Section, filename: r137.pmi8 wir0138 48.2 176 0.0 13.873 14.41 N/A 0.294654 22.6 76.7 22 74 30 18:44 22 Repeat WIR0137, filename: r138.pmi9 wir0139 47.4 176 0.0 13.874 14.412 N/A 0.104423 4.25 40.7 4 39 30 18:52 92 All Nozzles on, IRT air on, Collector Mechanixm in Test Section, filename: r139.pmi

10 wir0140 47.4 176 0.0 13.879 14.411 N/A 0.106158 4.31 40.6 4 39 30 18:54 92 Repeat WIR0139, filename: r140.pmi11 wir0141 44.8 176 0.0 13.875 14.411 N/A 0.641064 43.4 67.7 44 67 30 18:59 12 Nozzle #11 off, IRT air on, Collector Mechanism in Test Section, filename: r141.pmi12 wir0142 46.1 175 0.0 13.876 14.409 N/A 0.643594 43.7 67.9 44 67 30 19:01 12 Repeat WIR0141, filename: r142.pmi13 wir0143 47.4 176 0.0 13.881 14.4 61.18 0.642121 43.6 67.9 44 67 30 20:21 12 Nozzle #11 off, IRT air on, Verigood 100 14 wir0144 46 175 0.0 13.871 14.415 59.2 0.638705 43.4 67.95 44 67 30 20:31 12 Nozzle #11 off, IRT air on, Verigood 100 15 wir0145 47 176 0.0 13.881 14.412 54.79 0.642963 43.4 67.5 44 67 30 20:40 12 Nozzle #11 off, IRT air on, Verigood 100 16 wir0146 45.1 175 0.0 13.88 14.415 59.81 0.640648 43.5 67.9 44 67 30 20:50 12 Nozzle #11 off, IRT air on, Whatman 3MM17 wir0147 46.3 176 0.0 13.884 14.413 52.42 0.641176 43.6 68.0 44 67 30 20:59 12 Nozzle #11 off, IRT air on, Whatman 3MM18 wir0148 47.1 175 0.0 13.884 14.412 51.81 0.294271 22.6 76.8 22 74 6 21:11 22 Nozzle #11 off, IRT air on, Verigood 100 19 wir0149 46.4 177 0.0 13.885 14.413 53.59 0.295812 22.6 76.4 22 74 6 21:22 22 Nozzle #11 off, IRT air on, Verigood 100 20 wir0150 46.6 176 0.0 13.879 14.41 48.00 0.293578 22.4 76.3 22 74 6 21:31 22 Nozzle #11 off, IRT air on, Verigood 100 21 wir0151 48.1 175 0.0 13.884 14.411 52.61 0.295039 22.6 76.6 22 74 6 21:39 22 Nozzle #11 off, IRT air on, Whatman 3MM22 wir0152 47.9 176 0.0 13.888 14.412 50.88 0.291123 22.3 76.6 22 74 6 21:49 22 Nozzle #11 off, IRT air on, Whatman 3MM23 wir0153 45.7 175 0.0 13.881 14.412 53.4 0.105727 4.32 40.86 4 39 3 22:04 92 All Nozzles on, IRT air on, Verigood 10024 wir0154 47.8 175 0.0 13.88 14.412 54.08 0.105651 4.3 40.7 4 39 3 22:13 92 All Nozzles on, IRT air on, Verigood 10025 wir0155 46.4 175 0.0 13.886 14.415 54.47 0.105651 4.3 40.7 4 39 3 22:22 92 All Nozzles on, IRT air on, Verigood 10026 wir0156 46.8 175 0.0 13.885 14.407 50.29 0.112745 4.6 40.8 4 39 3 22:30 92 All Nozzles on, IRT air on, Whatman 3MM27 wir0157 49.5 175 0.0 13.871 14.41 50.05 0.107606 4.4 40.89 4 39 3 22:37 92 All Nozzles on, IRT air on, Whatman 3MM28 wir0158 47.2 176 8.0 13.89 14.42 53 0.293194 22.4 76.4 22 74 6 23:04 22 Nozzle #11 off, IRT air on, Verigood 100 29 wir0159 45.1 175 8.0 13.877 14.421 59.86 0.29281 22.4 76.5 22 74 6 23:12 22 Nozzle #11 off, IRT air on, Verigood 100 30 wir0160 45.5 176 8.0 13.886 14.423 52.29 0.29281 22.4 76.5 22 74 6 23:21 22 Nozzle #11 off, IRT air on, Verigood 100 31 wir0161 47.3 175 8.0 13.886 14.416 51.81 0.295958 22.7 76.7 22 74 6 23:28 22 Nozzle #11 off, IRT air on, Whatman 3MM32 wir0162 48.2 175 8.0 13.886 14.417 50.22 0.292969 22.5 76.8 22 74 6 23:35 22 Nozzle #11 off, IRT air on, Whatman 3MM

NASA/TM—2002-211700 385
Date : August 12, 1997 Note:

AVERAGE PBAR : 14.30 psia 1. Strip A (Verigood 100) is 36" above the floor, strip B (3MM) isDYE CONCENTRATION : 0.0003 grams/cc 38.5" above the floor.PSYCHROMETER READINGS : 2. Average 8 minutes per run

: 3. Pressure data of NACA652-415 was taken by IRT's Electro

 Scanned Pressure system. (Record #2215 ~~ #2244)4. Test Model : NACA 652-415

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION DISK DISPLAY TANK TIME REMARKS

PRESSURE READING PRESSURE

RUN Run I.D. Air TAS A.O.A P∞ PRESS Humidity PAIR PAIR PWATER PAIR PWATER SPRAY CLOCK MVD

NO. TEMP. (MPH) (deg.) (PSIA) TOTAL % PWATER Display Display Gauge Gauge TIME TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) (PSIA) (psig) (psig) (psig) (psig) (sec) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0163 44.8 174 0.0 13.781 14.31 63.1 0.108374 4.4 40.6 4 39 3 19:49 92 All Nozzles on, IRT air on2 wir0164 47.5 176 0.0 13.714 14.313 62 0.105392 4.3 40.8 4 39 3 19:58 92 All Nozzles on, IRT air on3 wir0165 42.6 175 0.0 13.783 14.319 73.07 0.107711 4.33 40.2 4 39 3 20:05 92 All Nozzles on, IRT air on4 wir0166 44 176 0.0 13.776 14.313 67 0.107975 4.4 40.75 4 39 3 20:12 92 All Nozzles on, IRT air on5 wir0167 47.6 175 8.0 13.709 14.309 65 0.106863 4.36 40.8 4 39 3 20:20 92 All Nozzles on, IRT air on6 wir0168 51.1 175 8.0 13.782 14.304 68.21 0.106388 4.33 40.7 4 39 3 20:28 92 All Nozzles on, IRT air on7 wir0169 50.7 174 8.0 13.79 14.309 64 0.107011 4.35 40.65 4 39 3 20:35 92 All Nozzles on, IRT air on8 wir0170 49.6 175 8.0 13.781 14.307 66 0.104156 4.26 40.9 4 39 3 20:43 92 All Nozzles on, IRT air on9 wir0171 49.4 176 8.0 13.797 14.311 61.94 0.633751 43.0 67.85 44 67 30 20:53 12 Nozzle #11 off, IRT air on

10 wir0172 50.7 176 8.0 14.702 14.311 55.69 0.641593 43.5 67.8 44 67 30 21:02 12 Nozzle #11 off, IRT air on11 wir0173 49.7 176 8.0 13.79 14.31 68 0.643491 43.5 67.6 44 67 30 21:10 12 Nozzle #11 off, IRT air on12 wir0174 47.7 175 8.0 13.788 14.308 65.07 0.641176 43.6 68.0 44 67 30 21:18 12 Nozzle #11 off, IRT air on13 wir0175 49.3 176 0.0 13.781 14.306 55.4 0.631732 43.4 68.7 44 67 30 21:26 12 Nozzle #11 off, IRT air on14 wir0176 48.6 175 0.0 13.787 14.307 58.8 0.643579 43.3 67.28 44 67 30 21:34 12 Nozzle #11 off, IRT air on15 wir0177 47.4 174 0.0 13.776 14.309 61.0 0.642647 43.7 68.0 44 67 30 21:42 12 Nozzle #11 off, IRT air on (results are not good, verigood 100 paper looks bad)16 wir0178 48.9 176 0.0 13.771 14.308 53.2 0.638643 43.3 67.8 44 67 30 21:54 12 Nozzle #11 off, IRT air on17 wir0179 48.4 174 0.0 13.776 14.306 59.03 0.643068 43.6 67.8 44 67 30 22:04 12 Nozzle #11 off, IRT air on18 wir0180 47.1 176 0.0 13.771 14.3 62.23 0.299213 22.8 76.2 22 74 6 22:17 22 Nozzle #11 off, IRT air on19 wir0181 49.1 175 0.0 13.764 14.296 55.18 0.298177 22.9 76.8 22 74 6 22:24 22 Nozzle #11 off, IRT air on20 wir0182 48.7 176 0.0 13.774 14.299 52.74 0.296654 22.7 76.52 22 74 6 22:31 22 Nozzle #11 off, IRT air on21 wir0183 47.7 175 0.0 13.761 14.296 56.01 0.297262 22.8 76.7 22 74 6 22:37 22 Nozzle #11 off, IRT air on22 wir0184 49.0 176 8.0 13.76 14.297 52.0 0.29765 22.8 76.6 22 74 6 22:45 22 Nozzle #11 off, IRT air on23 wir0185 49.2 176 8.0 13.776 14.285 50.0 0.296875 22.8 76.8 22 74 6 22:51 22 Nozzle #11 off, IRT air on24 wir0186 49.0 175 8.0 13.77 14.292 50.0 0.296875 22.8 76.8 22 74 6 22:59 22 Nozzle #11 off, IRT air on25 wir0187 49.4 177 8.0 13.754 14.291 49.0 0.284238 22.0 77.4 22 74 6 23:06 22 Nozzle #11 off, IRT air on

NASA/TM—2002-211700 386
Date : August 13, 1997

AVERAGE PBAR : 14.30 psia Note:DYE CONCENTRATION : 0.0003 grams/cc 1. Ideal condition: a) south vent door open half inchesPSYCHROMETER READINGS : b) total temperature 45 -- 50 deg.

: c) humidity from 75% to 85%

 2. Test Model: NACA 652-415

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION DISK DISPLAY TANK TIME REMARKS

PRESSURE READING PRESSURE

RUN Run I.D. Air TAS A.O.A P∞ PRESS Humidity PAIR PAIR PWATER PAIR PWATER SPRAY CLOCK MVD

NO. TEMP. (MPH) (deg.) (PSIA) TOTAL % PWATER Display Display Gauge Gauge TIME TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) (PSIA) (psig) (psig) (psig) (psig) (sec) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0188 49.2 174 8.0 13.772 14.299 72.9 0.645066 43.8 67.9 44 67 30 16:42 12 Nozzle #11 off, IRT air on2 wir0189 46.2 175 8.0 13.779 14.3 65.87 0.639461 43.17 67.51 44 67 30 16:51 12 Nozzle #11 off, IRT air on3 wir0190 45.9 175 8.0 13.778 14.301 64.5 0.627224 42.3 67.44 44 67 30 17:00 12 Nozzle #11 off, IRT air on4 wir0191 47.1 175 8.0 13.781 14.303 67.53 0.644444 43.5 67.5 44 67 30 17:08 12 Nozzle #11 off, IRT air on5 wir0192 45.3 174 8.0 13.775 14.298 72.07 0.641593 43.5 67.8 44 67 30 17:16 12 Nozzle #11 off, IRT air on6 wir0193 46.2 175 8.0 13.787 14.302 58.41 0.646972 43.8 67.7 44 67 30 17:23 12 Nozzle #11 off, IRT air on7 wir0194 47.7 175 8.0 13.775 14.296 66.0 0.644756 43.65 67.7 44 67 30 17:31 12 Nozzle #11 off, IRT air on8 wir0195 48.4 172 8.0 13.777 14.3 64.65 0.644018 43.6 67.7 44 67 30 17:38 12 Nozzle #11 off, IRT air on9 wir0196 47.6 174 8.0 13.781 14.299 65.45 0.641176 43.6 68.0 44 67 30 17:45 12 Nozzle #11 off, IRT air on

10 wir0197 49.1 176 8.0 13.788 14.304 60.94 0.643917 43.4 67.4 44 67 30 17:53 12 Nozzle #11 off, IRT air on11 wir0198 61.0 176 8.0 13.788 14.303 61.77 0.640761 43.45 67.81 44 67 30 18:39 12 Nozzle #11 off, IRT air on12 wir0199 37.0 176 8.0 13.773 14.3 80.0 #VALUE!   44 67 30 19:25 92 Nozzle #11 off, IRT air on13 wir0200 36.8 174 8.0 13.765 14.303 58.35 0.646018 43.8 67.8 44 67 30 19:49 92 Nozzle #11 off, IRT air on14 wir0201 39.7 173 8.0 13.771 14.304 75.76 0.644543 43.7 67.8 44 67 30 19:58 12 Nozzle #11 off, IRT air on15 wir0202 36.8 174 8.0 13.776 14.303 97.5 0.639053 43.2 67.6 44 67 30 20:07 12 Nozzle #11 off, IRT air on (both vent doors opened about 2' each, cloud observed) 16 wir0203 35.4 174 8.0 13.765 14.298 96.19 0.64497 43.6 67.6 44 67 30 20:17 12 Nozzle #11 off, IRT air on (south vent door open for 8", no cloud observed) 17 wir0204 42.3 174 8.0 13.788 14.312 85.77 0.638002 43.55 68.26 44 67 30 21:28 12 Nozzle #11 off, IRT air on (vent doors are closed), 3MM penetrated18 wir0205 46.9 176 8.0 13.776 14.306 81.0 0.639824 43.54 68.05 44 67 30 21:37 12 Nozzle #11 off, IRT air on (south vent door has half inches gap)19 wir0206 48.3 172 8.0 13.805 14.312 85.0 0.634841 43.22 68.08 44 67 20 21:47 12 Nozzle #11 off, IRT air on (south vent door has half inches gap)20 wir0207 50.1 174 8.0 13.786 14.306 75.12 0.644874 43.4 67.3 44 67 25 21:57 12 Nozzle #11 off, IRT air on (south vent door has half inches gap)21 wir0208 48.8 175 8.0 13.79 14.31 89.04 0.115196 4.7 40.8 4 39 3 22:13 92 All Nozzles on, IRT air on (south vent door has half inches gap)22 wir0209 47.2 175 8.0 13.778 14.313 80.7 0.110294 4.5 40.8 4 39 3 22:20 92 All Nozzles on, IRT air on (south vent door has half inches gap)23 wir0210 40.7 174 8.0 13.772 14.311 85.0 0.640351 43.8 68.4 44 67 25 22:35 12 Nozzle #11 off, IRT air on (both vent doors opened about 2' each, cloud observed)24 wir0211 46.4 175 8.0 13.788 14.316 92.0 0.644444 43.5 67.5 44 67 25 22:43 12 Nozzle #11 off, IRT air on (both vent doors opened about 2' each, cloud observed)25 wir0212 42.9 177 8.0 13.791 14.319 86.2 0.64645 43.7 67.6 44 67 25 22:50 12 Nozzle #11 off, IRT air on (both vent doors opened about 2' each, cloud observed)26 wir0213 45.5 174 0.0 13.79 14.309 77.0 0.645066 43.8 67.9 44 67 25 23:00 12 Nozzle #11 off, IRT air on (both vent doors opened about 2' each, cloud observed)27 wir0214 44.7 174 0.0 13.794 14.318 82.2 0.646972 43.8 67.7 44 67 25 23:07 12 Nozzle #11 off, IRT air on (both vent doors opened about 2' each, cloud observed)28 wir0215 45.6 176 0.0 13.79 14.32 80.1 0.643382 43.75 68.0 44 67 25 23:13 12 Nozzle #11 off, IRT air on (both vent doors opened about 2' each, cloud observed)

NASA/TM—2002-211700 387
Date : August 14, 1997

AVERAGE PBAR : 14.30 psiaDYE CONCENTRATION : 0.0003 grams/ccPSYCHROMETER READINGS : Note:

: 1. Test Model: Boeing 757 Tailplane Airfoil (stall @ -9 deg.)

 2. Pressure data was taken from IRT's ESP system

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION DISK DISPLAY TANK TIME REMARKS

PRESSURE READING PRESSURE

RUN Run I.D. Air TAS A.O.A P∞ PRESS Humidity PAIR PAIR PWATER PAIR PWATER SPRAY CLOCK MVD

NO. TEMP. (MPH) (deg.) (PSIA) TOTAL % PWATER Display Display Gauge Gauge TIME TIME **  IRT 80 lbs air when tunnel was in operating condition

(oF) (PSIA) (psig) (psig) (psig) (psig) (sec) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0216 47.4 176 0.0 13.792 14.271 73.6 0.643594 43.7 67.9 44 67 25 19:40 12 Nozzle #11 off, IRT air on (south vent door opens 13 inches)2 wir0217 48.4 176 0.0 13.741 14.276 78.7 0.645066 43.8 67.9 44 67 25 19:54 12 Nozzle #11 off, IRT air on (south vent door opens 16 inches)3 wir0218 46.0 176 0.0 13.745 14.236 80.64 0.646539 43.9 67.9 44 67 25 20:03 12 Nozzle #11 off, IRT air on (south vent door opens 21 inches)4 wir0219 46.2 175 0.0 13.751 14.277 76.7 0.646539 43.9 67.9 44 67 25 20:10 12 Nozzle #11 off, IRT air on (south vent door opens 21 inches)5 wir0220 45.1 174 4.0 13.747 14.276 78.17 0.627507 43.8 69.8 44 67 25 20:27 12 Nozzle #11 off, IRT air on (south vent door opens 31 inches)6 wir0221 44.5 176 4.0 13.755 14.279 80.6 0.640118 43.4 67.8 44 67 25 20:35 12 Nozzle #11 off, IRT air on (south vent door opens 31 inches)7 wir0222 46.2 175 4.0 13.745 14.277 72.4 0.639053 43.2 67.6 44 67 25 20:47 12 Nozzle #11 off, IRT air on (south vent door opens 31", north vent door opens 12")8 wir0223 44.1 174 4.0 13.76 14.277 82.2 0.645803 43.85 67.9 44 67 25 20:54 12 Nozzle #11 off, IRT air on (south vent door opens 31", north vent door opens 12")9 wir0224 46.4 175 4.0 13.748 14.278 78.5 0.292555 22.4 76.4 22 74 6 21:12 22 Nozzle #11 off, IRT air on (south vent door opens 31", north vent door opens 12")

10 wir0225 40.7 174 4.0 13.75 14.28 76.6 0.293045 22.5 76.78 22 74 6 21:23 22 Nozzle #11 off, IRT air on (both vent doors closed -- due to heavy cloud observed)11 wir0226 40.5 174 4.0 13.746 14.288 78.8 0.311111 23.8 76.5 22 74 6 21:31 22 Nozzle #11 off, IRT air on (vent doors were closed)12 wir0227 43.4 174 4.0 13.74 14.28 70.3 0.294654 22.6 76.7 22 74 6 21:41 22 Nozzle #11 off, IRT air on (south vent door opens 7")13 wir0228 47.9 175 0.0 13.744 14.28 70.5 0.291287 22.4 76.9 22 74 6 21:53 22 Nozzle #11 off, IRT air on (south vent door opens 17")14 wir0229 44.4 176 0.0 13.743 14.278 74.3 0.292428 22.4 76.6 22 74 6 22:01 22 Nozzle #11 off, IRT air on (south vent door opens 31")15 wir0230 43.1 177 0.0 13.729 14.277 78.7 0.29765 22.8 76.6 22 74 6 22:07 22 Nozzle #11 off, IRT air on (south vent door opens 31")16 wir0231 45.6 177 0.0 13.746 14.277 72.0 0.290314 22.18 76.4 22 74 6 22:13 22 Nozzle #11 off, IRT air on (south vent door opens 31")17 wir0232 43.1 177 0.0 13.749 14.285 75.7 0.104218 4.25 40.78 4 39 3 22:29 92 All Nozzles on, IRT air on ( both vent doors closed)18 wir0233 45.0 175 0.0 13.736 14.276 70.6 0.10489 4.29 40.9 4 39 3 22:38 92 All Nozzles on, IRT air on ( south vent door opens 22")19 wir0234 45.9 176 0.0 13.74 14.28 71.0 0.103704 4.2 40.5 4 39 3 22:45 92 All Nozzles on, IRT air on ( south vent door opens 14")

NASA/TM—2002-211700 388
Date : August 18, 1997

AVERAGE PBAR : 13.82 psia Note:DYE CONCENTRATION : 0.0003 grams/cc 1. Test Model: CollectorPSYCHROMETER READINGS : 2. Angle Of Attack in this record was refer to IRT's AOA setting

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION DISK DISPLAY TANK TIME REMARKS

PRESSURE READING PRESSURE

RUN Run I.D. Air TAS A.O.A P∞ PRESS Humidity PAIR PAIR PWATER PAIR PWATER SPRAY CLOCK MVD

NO. TEMP. (MPH) (deg.) (PSIA) TOTAL % PWATER Display Display Gauge Gauge TIME TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) IRT (psia) (psig) (psig) (psig) (psig) (sec) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0258 46.7 175 0.0 13.82 14.362 84.1 0.2937 22.5 76.6 22 74 6 18:08 22 Nozzle #11 off, IRT air on, Verigood 100 paper (south vent door opens 31")2 wir0259 47.4 175 0.0 13.84 14.36 82.2 0.2947 22.4 76.0 22 74 6 18:18 22 Nozzle #11 off, IRT air on, Verigood 100 paper (south vent door opens 31")3 wir0260 45.4 175 0.0 13.82 14.362 87.7 0.2943 22.6 76.8 22 74 6 18:27 22 Nozzle #11 off, IRT air on, Verigood 100 paper (south vent door opens 31")4 wir0261 45.7 178 0.0 13.82 14.36 97.0 0.2913 22.4 76.9 22 74 6 22 Nozzle #11 off, IRT air on, Whatman 3MM (south vent door opens 31")5 wir0262 50.7 175 0.0 13.82 14.36 87.0 0.2992 22.8 76.2 22 74 6 18:48 22 Nozzle #11 off, IRT air on, Whatman 3MM (south vent door opens 9")6 wir0263 52.7 176 0.0 13.81 14.35 72.0 0.6412 43.6 68.0 44 67 25 19:22 12 Nozzle #11 off, IRT air on, Verigood 100 paper (south vent door opens 9")7 wir0264 46.5 176 0.0 13.82 14.36 73.9 0.6435 43.5 67.6 44 67 25 19:37 12 Nozzle #11 off, IRT air on, Verigood 100 paper (south vent door opens 17")8 wir0265 42.7 175 0.0 13.82 14.35 83.0 0.6421 43.6 67.9 44 67 25 19:44 12 Nozzle #11 off, IRT air on, Verigood 100 paper (vent doors closed)9 wir0266 50.6 175 0.0 13.83 14.36 75.5 0.6382 43.4 68.0 44 67 25 19:52 12 Nozzle #11 off, IRT air on, Whatman 3MM (vent doors close)

10 wir0267 39.4 173 0.0 13.83 14.36 85.0 0.644 43.6 67.7 44 67 25 20:01 12 Nozzle #11 off, IRT air on, Whatman 3MM (vent doors closed)11 wir0268 43.2 175 0.0 13.83 14.36 83.4 0.105 4.23 40.3 4 39 3 20:38 92 All Nozzles on, IRT air on, Verigood 100 paper (vent doors closed)12 wir0269 44.1 176 0.0 13.82 14.36 74.7 0.1059 4.3 40.6 4 39 3 20:45 92 All Nozzles on, IRT air on, Verigood 100 paper (vent doors closed)13 wir0270 43.4 175 0.0 13.83 14.36 73.7 0.101 4.1 40.6 4 39 3 20:54 92 All Nozzles on, IRT air on, Verigood 100 paper (vent doors closed)14 wir0271 49.8 176 0.0 13.82 14.36 66.2 0.1027 4.2 40.9 4 39 3 21:02 92 All Nozzles on, IRT air on, Whatman 3MM paper (vent doors closed)15 wir0272 51.6 176 0.0 13.84 14.37 69.0 0.1078 4.4 40.8 4 39 3 21:10 92 All Nozzles on, IRT air on, Whatman 3MM paper (vent doors closed)16 wir0273 50.9 177 0.0 13.83 14.37 62.0 0.2995 23.0 76.8 22 74 6 21:27 22 Nozzle #11 off, IRT air on, Verigood 100 paper ( vent doors closed)17 wir0274 47.7 175 0.0 13.87 14.37 70.0 0.2889 22.3 77.20 22 74 6 21:43 22 Nozzle #11 off, IRT air on, Verigood 100 paper ( vent doors closed)18 wir0275 51.1 176 -8.0 13.84 14.36 74.5 0.292 22.4 76.7 22 74 6 22:13 22 Nozzle #11 off, IRT air on, Verigood 100 paper (south vent door opens 12")19 wir0276 46.2 176 -8.0 13.84 14.36 73.6 0.2961 22.8 77.0 22 74 6 22:20 22 Nozzle #11 off, IRT air on, Verigood 100 paper (south vent door opens 12")20 wir0277 45.6 175 -8.0 13.83 14.36 70.6 0.3059 23.4 76.5 22 74 6 22:36 22 Nozzle #11 off, IRT air on, Verigood 100 paper (south vent door opens 25")21 wir0278 45.1 176 -8.0 13.82 14.36 73.6 0.2917 22.4 76.8 22 74 6 22:44 22 Nozzle #11 off, IRT air on, Whatman 3MM paper (south vent door opens 25")22 wir0279 42.2 176 -8.0 13.83 14.36 81.6 0.2939 22.6 76.9 22 74 6 22:52 22 Nozzle #11 off, IRT air on, Whatman 3MM paper (south vent door opens 25")

NASA/TM—2002-211700 389
Date : August 19, 1997 Note:

AVERAGE PBAR : 13.80 psia 1. Test Model: CollectorDYE CONCENTRATION : 0.0003 grams/cc 2. Angle Of Attack in this record was refer to IRT's AOA settingPSYCHROMETER READINGS : 3. Humidity on IRT was low, all 10 IRT's spray bars were set to

: spray to increase the humidity inside the IRT

4. Pre-spray the tunnel for about 1.5 min to 2. min before placing the strips on the collector -- to increase the humidity in IRT

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION DISK DISPLAY TANK TIME REMARKS

PRESSURE READING PRESSURE

RUN Run I.D. Air TAS IRT P∞ PRESS Humidity PAIR PAIR PWATER PAIR PWATER SPRAY CLOCK MVD

NO. TEMP. (MPH) A.O.A. (psia) TOTAL % PWATER Display Display Gauge Gauge TIME TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) (deg) (psia) (psig) (psig) (psig) (psig) (sec) ** IRT 20 lbs air when tunnel was in idle condition

bad wir280-a 44.2 177 -8.0 13.7 14.3 76.0 0.6381 43.2 67.7 44 67 25 18:02 12 Nozzle #11 off, IRT air on, Verigood 100 paper (vent doors closed), trial run

1 wir0280 46.2 176 -8.0 13.79 14.33 81.5 0.6392 43.4 67.9 44 67 25 18:26 12 Nozzle #11 off, IRT air on, Verigood 100 paper (vent doors closed)2 wir0281 48.6 175 -8.0 13.81 14.33 80.5 0.6368 43.3 68.0 44 67 25 18:34 12 Nozzle #11 off, IRT air on, Verigood 100 paper (vent doors closed)3 wir0282 49.2 177 -8.0 13.81 14.33 69.9 0.6368 43.3 68.0 44 67 25 18:42 12 Nozzle #11 off, IRT air on, Verigood 100 paper (IRT spray for 7 min., vent doors closed)4 wir0283 49.1 176 -8.0 13.81 14.32 77.8 0.6436 43.7 67.9 44 67 25 19:03 12 Nozzle #11 off, IRT air on, Whatman 3MM paper (vent doors closed)5 wir0284 50.1 176 -8.0 13.8 14.33 67.0 0.6431 43.6 67.8 44 67 25 19:11 12 Nozzle #11 off, IRT air on, Whatman 3MM paper (vent doors closed)6 wir0285 49.2 178 -8.0 13.79 14.33 73.2 0.1098 4.5 41.0 4 39 3 19:29 92 All Nozzles on, IRT air on, Verigood 100 paper (IRT spray for 3 min, vent doors closed)7 wir0286 50.9 175 -8.0 13.8 14.33 67.9 0.1027 4.2 40.9 4 39 3 19:37 92 All Nozzles on, IRT air on, Verigood 100 paper (vent doors closed)8 wir0287 50.4 176 -8.0 13.8 14.33 59.4 0.1051 4.3 40.9 4 39 3 19:45 92 All Nozzles on, IRT air on, Verigood 100 paper (vent doors closed)9 wir0288 49.6 176 -8.0 13.79 14.32 79.2 0.1073 4.4 41.0 4 39 3 20:02 92 All Nozzles on, IRT air on, Whatman 3MM paper (IRT spray for 7 min, vent doors closed)

10 wir0289 50.5 176 -8.0 13.8 14.32 64.1 0.1073 4.4 41.0 4 39 3 20:10 92 All Nozzles on, IRT air on, Whatman 3MM paper (vent doors closed)11 wir0290 48.8 176 +8.0 13.79 14.32 76.0 0.1037 4.2 40.5 4 39 3 20:39 92 All Nozzles on, IRT air on, Verigood 100 paper (IRT spray for 8 min, vent doors closed)12 wir0291 51.2 176 +8.0 13.79 14.32 72.5 0.1073 4.4 41.0 4 39 3 20:46 92 All Nozzles on, IRT air on, Verigood 100 paper (vent doors closed)13 wir0292 51.2 175 +8.0 13.79 14.36 59.9 0.1051 4.3 40.9 4 39 3 20:53 92 All Nozzles on, IRT air on, Verigood 100 paper (vent doors closed)14 wir0293 47.7 175 +8.0 13.8 14.32 75.7 0.1078 4.4 40.8 4 39 3 21:10 92 All Nozzles on, IRT air on, Whatman 3MM paper (IRT spray for 8 min, vent doors closed)15 wir0294 49.3 175 +8.0 13.8 14.32 66.5 0.1073 4.4 41.0 4 39 3 21:16 92 All Nozzles on, IRT air on, Whatman 3MM paper (vent doors closed)16 wir0295 47.3 176 +8.0 13.79 14.32 74.0 0.6362 43.31 68.08 44 67 25 21:33 12 Nozzle #11 off, IRT air on, Verigood 100 paper (IRT spray for 10 min, vent doors closed)17 wir0296 50.2 175 +8.0 13.8 14.32 91.5 0.6346 43.6 68.70 44 67 25 21:48 12 Nozzle #11 off, IRT air on, Verigood 100 paper (IRT spray for 10 min, vent doors closed)18 wir0297 50.1 176 13.8 13.79 14.32 72.5 0.637 43.7 68.6 44 67 25 21:55 12 Nozzle #11 off, IRT air on, Verigood 100 paper (vent doors closed)19 wir0298 49.9 176 +8.0 13.81 14.32 62.8 0.6332 43.11 68.1 44 67 25 22:01 12 Nozzle #11 off, IRT air on, Verigood 100 paper (vent doors closed)20 wir0299 50.6 175 +8.0 13.8 14.32 76.3 0.6406 43.5 67.9 44 67 25 22:08 12 Nozzle #11 off, IRT air on, Verigood 100 paper (Colin Bidwell Humidity Technique, see note 4)21 wir0300 50.0 176 +8.0 13.8 14.32 73.0 0.289 22.26 77.02 22 74 6 22:17 22 Nozzle #11 off, IRT air on, Verigood 100 paper (Colin Bidwell Humidity Technique, see note 4)22 wir0301 49.9 177 +8.0 13.78 14.32 80.0 0.2927 22.3 76.2 22 74 6 22:25 22 Nozzle #11 off, IRT air on, Verigood 100 paper (Colin Bidwell Humidity Technique, see note 4)23 wir0302 50.1 176 +8.0 13.8 14.32 68.2 0.298 22.8 76.5 22 74 6 22:32 22 Nozzle #11 off, IRT air on, Verigood 100 paper (Colin Bidwell Humidity Technique, see note 4)24 wir0303 49.3 177 +8.0 13.8 14.32 80.0 0.29 22.3 76.9 22 74 6 22:44 22 Nozzle #11 off, IRT air on, Verigood 100 paper (Colin Bidwell Humidity Technique, see note 4)25 wir0304 49.0 176 +8.0 13.79 14.32 74.2 0.294 22.7 77.2 22 74 6 22:52 22 Nozzle #11 off, IRT air on, Verigood 100 paper (Colin Bidwell Humidity Technique, see note 4)

NASA/TM—2002-211700 390
Date : August 20, 1997 Note:

AVERAGE PBAR : 13.66 psia 1. Test Model: GLC 305DYE CONCENTRATION : 0.0003 grams/cc 2. GLC 305 pressure data was taken by IRT's ESP systemPSYCHROMETER READINGS : 3. Angle Of Attack in this record was refer to IRT's AOA setting

: 4. GLC 305's AOA is same as IRT Turntable's AOA

5. New spray time set to 18 seconds for 12 MVD

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION DISK DISPLAY TANK TIME REMARKS

PRESSURE READING PRESSURE

RUN Run I.D. Air TAS IRT P∞ PRESS Humidity PAIR PAIR PWATER PAIR PWATER SPRAY CLOCK MVD

NO. TEMP. (MPH) A.O.A. (psia) TOTAL % PWATER Display Display Gauge Gauge TIME TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) (deg) (psia) (psig) (psig) (psig) (psig) (sec) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0305 45.3 175 1.5 13.68 14.21 73.4 0.2981 22.3 74.8 22 74 6 18:25 22 Nozzle #11 off, IRT air on (both vent doors closed)

2 wir0306 43.6 176 1.5 13.68 14.2 70.8 0.29 22.3 76.9 22 74 6 18:35 22 Nozzle #11 off, IRT air on (both vent doors closed)3 wir0307 44.3 177 1.5 13.67 14.2 68.2 0.2957 22.8 77.1 22 74 6 18:42 22 Nozzle #11 off, IRT air on (both vent doors closed)4 wir0308 44.1 175 1.5 13.68 14.21 73.6 0.2935 22.6 77.0 22 74 6 18:55 22 Nozzle #11 off, IRT air on (both vent doors closed)5 wir0309 45.4 177 6.0 13.66 14.2 73.6 0.2943 22.6 76.8 22 74 6 19:06 22 Nozzle #11 off, IRT air on (south vent doors open 11")6 wir0310 45.3 176 6.0 13.68 14.21 77.1 0.2935 22.6 77.0 22 74 6 19:13 22 Nozzle #11 off, IRT air on (both vent doors closed)7 wir0311 44.7 176 6.0 13.67 14.21 70.4 0.2965 22.8 76.9 22 74 6 19:20 22 Nozzle #11 off, IRT air on (both vent doors closed)8 wir0312 44.3 177 6.0 13.68 14.21 68.7 0.2962 22.6 76.3 22 74 6 19:27 22 Nozzle #11 off, IRT air on (both vent doors colsed)9 wir0313 42.5 176 6.0 13.66 14.2 85.5 0.6397 43.5 68.0 44 67 18 19:37 12 Nozzle #11 off, IRT air on (south vent doors open 11")

10 wir0314 43.9 177 6.0 13.66 14.2 77.1 0.6416 43.5 67.8 44 67 18 19:44 12 Nozzle #11 off, IRT air on (south vent doors open 5")11 wir0315 44.9 175 6.0 13.66 14.2 74.9 0.6412 43.6 68.0 44 67 18 19:51 12 Nozzle #11 off, IRT air on (south vent doors open 5")12 wir0316 44.4 176 6.0 13.67 14.2 76.7 0.6444 43.5 67.5 44 67 18 19:57 12 Nozzle #11 off, IRT air on (south vent doors open 6")13 wir0317 44.0 177 1.5 13.66 14.2 75.3 0.644 43.6 67.7 44 67 18 20:03 12 Nozzle #11 off, IRT air on (south vent doors open 6")14 wir0318 44.6 177 1.5 13.66 14.2 82.1 0.6426 43.7 68.0 44 67 18 20:15 12 Nozzle #11 off, IRT air on (south vent doors open 11")15 wir0319 43.1 176 1.5 13.66 14.2 81.6 0.6456 43.9 68 44 67 18 20:27 12 Nozzle #11 off, IRT air on (south vent doors open 15")16 wir0320 42.1 176 1.5 13.67 14.2 81.0 0.6406 43.5 67.9 44 67 18 20:34 12 Nozzle #11 off, IRT air on (south vent doors open 5")17 wir0321 43.0 177 1.5 13.67 14.2 82.4 0.1034 4.20 40.6 4 39 3 20:49 92 All Nozzles on, IRT air on, (south vent doors open 5")18 wir0322 41.7 176 1.5 13.67 14.2 81.5 0.1034 4.2 40.6 4 39 3 20:57 92 All Nozzles on, IRT air on, (south vent doors open 5")19 wir0323 42.2 175 1.5 13.66 14.2 79.4 0.1039 4.25 40.9 4 39 3 21:03 92 All Nozzles on, IRT air on, (south vent doors open 5")20 wir0324 41.6 177 1.5 13.67 14.2 79.4 0.1032 4.22 40.9 4 39 3 21:10 92 All Nozzles on, IRT air on, (south vent doors open 5")21 wir0325 41.8 175 6.0 13.66 14.2 78.8 0.1057 4.3 40.7 4 39 3 21:16 92 All Nozzles on, IRT air on, (south vent doors open 5")22 wir0326 41.7 177 6.0 13.66 14.2 78.3 0.1051 4.3 40.9 4 39 3 21:23 92 All Nozzles on, IRT air on, (south vent doors open 5")23 wir0327 41.3 177 6.0 13.67 14.2 79.3 0.1054 4.3 40.8 4 39 3 21:29 92 All Nozzles on, IRT air on, (south vent doors open 5")24 wir0328 41.9 176 6.0 13.67 14.2 75.1 0.1051 4.3 40.9 4 39 3 21:35 92 All Nozzles on, IRT air on, (south vent doors open 5")25 wir0329 42.9 175 1.5 13.67 14.2 77.3 0.2904 22.3 76.8 22 74 10 21:50 22 Nozzle #11 off, IRT air on -- test for Colin Bidwell, Part I26 wir0330 43.4 176 1.5 13.67 14.2 75.6 0.292 22.4 76.7 22 74 10 21:52 22 repeat WIR0329 except All Nozzle on27 wir0331 41.2 176 1.5 13.67 14.2 75.3 0.2973 22.8 76.7 22 74 10 21:55 22 repeat WIR0330 except Nozzle #11 off28 wir0332 41.3 175 1.5 13.67 14.2 78.1 0.2915 22.3 76.5 22 74 10 21:58 22 repeat WIR0331

NASA/TM—2002-211700 391
Date : August 21, 1997 Note:

AVERAGE PBAR : 13.66 psia 1. Test Model: Collector MechanismDYE CONCENTRATION : 0.0003 grams/ccPSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION DISK DISPLAY TANK TIME REMARKS

PRESSURE READING PRESSURE

RUN Run I.D. Air TAS IRT P∞ PRESS Humidity PAIR PAIR PWATER PAIR PWATER SPRAY CLOCK MVD

NO. TEMP. (MPH) A.O.A. (psia) TOTAL % PWATER Display Display Gauge Gauge TIME TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) (deg) (psia) (psig) (psig) (psig) (psig) (sec) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0333 41.7 174 0.0 13.71 14.24 93.1 0.6456 43.9 68.0 44 67 18 17:09 12 Nozzle #11 off, IRT air on (vent doors closed)

2 wir0334 43.1 176 0.0 13.7 14.23 84.3 0.6426 43.7 68.0 44 67 18 17:18 12 Nozzle #11 off, IRT air on (vent doors closed)3 wir0335 45.3 174 0.0 13.72 14.24 83.2 0.6412 43.6 68.0 44 67 18 17:32 12 Nozzle #11 off, IRT air on (vent doors closed)4 wir035-a 49.3 174 0.0 13.72 14.23 67.0 0.6354 43.48 68.4 44 67 18 17:41 12 Nozzle #11 off, IRT air on (vent doors closed)5 wir0336 42.0 175 0.0 13.7 14.23 84.4 0.2956 22.7 76.8 22 74 6 17:54 22 Nozzle #11 off, IRT air on (vent doors closed)6 wir0337 43.7 174 0.0 13.71 14.23 80.1 0.2984 22.8 76.4 22 74 6 18:00 22 Nozzle #11 off, IRT air on (vent doors closed)7 wir0338 46.4 174 0.0 13.72 14.23 77.6 0.1032 4.23 41.0 4 39 3 18:42 92 All Nozzles on, IRT air on (vent doors closed)8 wir0339 48.0 175 0.0 13.7 14.23 74.0 0.1051 4.3 40.9 4 39 3 18:49 92 All Nozzles on, IRT air on (vent doors closed)9 wir0340 48.0 175 -8.0 13.71 14.23 72.0 0.6406 43.5 67.9 44 67 18 19:06 12 Nozzle #11 off, IRT air on (vent doors closed)

10 wir0341 45.1 177 -8.0 13.69 14.23 70.9 0.6402 43.6 68.1 44 67 18 19:24 12 Nozzle #11 off, IRT air on (south vent door opens )11 wir0342 41.0 176 -8.0 13.67 14.22 94.4 0.6426 43.7 68.0 44 67 18 19:42 12 Nozzle #11 off, IRT air on (pre-spray and then open south vent door 10")12 wir0343 42.5 174 -8.0 13.7 14.22 76.8 0.2943 22.6 76.8 22 74 6 19:56 22 Nozzle #11 off, IRT air on (south vent door opens 10")13 wir0344 43.3 176 -8.0 13.7 14.22 74.1 0.296 22.7 76.7 22 74 6 20:04 22 Nozzle #11 off, IRT air on (south vent door opens 10")14 wir0345 43.8 175 -8.0 13.7 14.23 65.7 0.1078 4.4 40.8 4 39 3 20:15 92 All Nozzles on, IRT air on (vent doors closed)15 wir0346 39.8 176 -8.0 13.7 14.23 75.6 0.1054 4.3 40.8 4 39 3 20:24 92 All Nozzles on, IRT air on (vent doors closed)16 wir0347 42.7 176 +8.0 13.69 14.23 74.6 0.6397 43.5 68.0 44 67 18 20:48 12 Nozzle #11 off, IRT air on (vent doors closed)17 wir0348 43.2 174 +8.0 13.71 14.24 73.1 0.6397 43.5 68.0 44 67 18 21:01 12 Nozzle #11 off, IRT air on (pre-spray for 45 seconds, vent doors closed)18 wir0349 43.0 176 +8.0 13.71 14.23 70.9 0.6412 43.60 68.0 44 67 18 21:11 12 Nozzle #11 off, IRT air on (pre-spray for 30 seconds, vent doors closed)19 wir0350 43.5 176 +8.0 13.71 14.23 63.5 0.2947 22.6 76.7 22 74 6 21:19 22 Nozzle #11 off, IRT air on (vent doors closed)20 wir0351 42.5 175 +8.0 13.69 14.22 74.3 0.2932 22.4 76.4 22 74 6 21:29 22 Nozzle #11 off, IRT air on (vent doors closed)21 wir0352 43.2 178 +8.0 13.69 14.23 69.0 0.1117 4.57 40.9 4 39 3 21:40 92 All Nozzles on, IRT air on (vent doors closed, IRT air only 70 lb.)22 wir0353 43.6 173 +8.0 13.71 14.24 67.0 0.1081 4.4 40.7 4 39 3 21:51 92 All Nozzles on, IRT air on (pre-spray, vent doors closed)23 wir0354 40.2 175 +8.0 13.7 14.24 81.4 0.6499 43.8 67.4 44 67 5 22:00 12 Nozzle #11 off, IRT air on (vent doors closed)24 wir0355 41.3 176 +8.0 13.7 14.23 75.0 0.6451 43.8 67.9 44 67 10 22:09 12 Nozzle #11 off, IRT air on (south vent door open 11")25 wir0356 43.7 176 +8.0 13.7 14.23 77.0 0.6382 43.4 68.0 44 67 15 22:16 12 Nozzle #11 off, IRT air on (south vent door open 11")26 wir0357 42.1 176 +8.0 13.7 14.23 78.4 0.6425 43.5 67.7 44 67 20 22:23 12 Nozzle #11 off, IRT air on (south vent door open 11")

NASA/TM—2002-211700 392
Date : August 22, 1997 Note:

AVERAGE PBAR : 13.73 psia 1. LWC measurement test (Bob Ide)DYE CONCENTRATION : 0.0003 grams/ccPSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION DISK DISPLAY TANK TIME REMARKS

PRESSURE READING PRESSURE

RUN Run I.D. Air TAS IRT P∞ PRESS Humidity PAIR PAIR PWATER PAIR PWATER SPRAY CLOCK MVD "total temp recorded instead of static for wir 0358 thru 0376 

NO. TEMP. (MPH) A.O.A. (PSIA) TOTAL % PWATER Display Display Gauge Gauge TIME TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) (deg) (psia) (psig) (psig) (psig) (psig) (sec) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0358 58.1 177 0.0 13.73 14.27 70 0.6436 43.4 67.4 44 67 120 16:49 12 Nozzle #11 off, (vent doors closed) meas 11 mic, no IRT air2 wir0359 52.1 177 0.0 13.73 14.26 65 0.6439 43.4 67.4 44 67 120 16:55 12 Nozzle #11 off, (vent doors closed) meas 11 mic, no IRT air3 wir0360 49.7 177 0.0 13.73 14.27 68.0 0.2928 22.4 76.5 22 74 120 17:01 22 Nozzle #11 off, (vent doors closed) meas 19 mic, no IRT air4 wir0361 48.6 176 0.0 13.73 14.27 68.0 0.2954 22.6 76.5 22 74 120 17:05 22 Nozzle #11 off, (south vent door open 21`") meas 19 mic, no IRT air5 wir0362 49.3 175 0.0 13.73 14.27 81.0 0.2911 22.3 76.6 22 74 120 17:13 22 Nozzle #11 off, (south vent door open 21") meas 19 mic, no IRT air6 wir0363 49.1 175 0.0 13.73 14.27 78.0 0.6493 43.7 67.3 44 67 120 17:19 12 Nozzle #11 off, (south vent door open 21") meas 11 mic, no IRT air7 wir0364 49.4 177 0.0 13.73 14.27 82.0 0.6416 43.5 67.8 44 67 120 17:56 12 Nozzle #11 off, (south vent door open 21"), no IRT air , LWC = 0.12 g/cm38 wir0365 49.9 174 0.0 13.73 14.27 83.0 0.6436 43.7 67.9 44 67 120 18:03 12 Nozzle #11 off, IRT air on (south vent door open 21"), LWC = 0.07 g/cm39 wir0366 49.3 177 0.0 13.73 14.27 80.0 0.6435 43.5 67.6 44 67 120 18:11 12 Nozzle #11 off, IRT air on (south vent door open 21"), LWC = 0.06 to 0.07 g/cm3

10 wir0367 47.9 176 0.0 13.73 14.27 87.0 0.2915 22.3 76.5 22 74 120 18:17 22 Nozzle #11 off, IRT air on (south vent door open 21"), LWC = 0.17 to 0.21 g/cm311 wir0368 49.2 176 0.0 13.73 14.27 85.0 0.293 22.5 76.8 22 74 120 18:21 22 Nozzle #11 off, IRT air on (south vent door open 21"), LWC = 0.17 to 0.22 g/cm312 wir0369 49.1 176 0.0 13.74 14.27 85.0 0.1073 4.4 41.0 4 39 120 18:30 92 all Nozzles , IRT air on (south vent door open 21"), LWC = 0.22 to 0.26 g/cm313 wir0370 68.2 175 0.0 13.77 14.29 68.0 0.1069 4.35 40.7 4 39 60 19:34 92 all Nozzles , IRT air on ( vent doors closed), LWC = 0.16 to 0.2 g/cm314 wir0371 68.2 175 0.0 13.77 14.29 68.0 0.6459 43.6 67.5 44 67 60 19:38 12 Nozzle #11 off , IRT air on ( vent doors closed), LWC = 0.01 g/cm315 wir0372 68.7 175 0.0 13.77 14.29 67.0 0.2904 22.3 76.8 22 74 60 19:43 22 Nozzle #11 off , IRT air on ( vent doors closed), LWC = 0.04 to 0.06 g/cm316 wir0373 71.5 176 0.0 13.78 14.29 61.0 0.293 22.5 76.8 22 74 60 20:01 22 Nozzle #11 off , IRT air on ( vent doors closed), LWC = 0.03 to 0.04 g/cm317 wir0374 72.1 176 0.0 13.78 14.29 60.0 0.6522 43.7 67.0 44 67 80 20:05 12 Nozzle #11 off , IRT air on ( vent doors closed), LWC = 0.0 to 0.005 g/cm318 wir0375 72.9 175 0.0 13.78 14.29 58.0 0.1051 4.30 40.9 4 39 80 20:10 92 all Nozzles , IRT air on ( vent doors closed), LWC = 0.14 to 0.18 g/cm319 wir0376 65.0 175 0.0 13.78 14.29 50.0 0.115 4.6 40.0 4 39 80 20:19 92 all Nozzles , IRT air on ( vent doors closed), LWC = 0.16 to 0.20 g/cm320 wir0377 41.0 174 0.0 13.75 14.29 55.0 0.0983 4.0 40.7 4 39 80 20:30 92 All Nozzles on, IRT air on (vent doors closed), LWC = 0.16 to 0.2 g/cm321 wir0378 38.7 175 0.0 13.76 14.29 60.0 0.2911 22.3 76.6 22 74 80 20:35 22 Nozzle #11 off, IRT air on (vent doors closed), Total T. = 44.7, LWC = 0.11 to 0.112 g/cm322 wir0379 38.7 176 0.0 13.74 14.29 66.0 0.2906 22.2 76.4 22 74 80 20:50 22 Nozzle #11 off , IRT air on (south vent door open 15"), LWC = 0.12 to 0.16 g/cm323 wir0380 38.2 176 0.0 13.75 14.29 74.0 0.2906 22.2 76.4 22 74 80 20:52 22 Nozzle #11 off , IRT air on (south vent door open 15"), LWC = 0.14 to 0.18 g/cm324 wir0381 40.5 176 0.0 13.75 14.29 80.0 0.2913 22.2 76.2 22 74 80 20:54 22 Nozzle #11 off , IRT air on ( south vent door open 15"), LWC = 0.14 to 0.18 g/cm325 wir382 no data recorded26 wir0383 39.0 176 0.0 13.74 14.29 91.0 0.2865 22 76.8 22 74 80 21:05 22 Nozzle #11 off , IRT air on ( south vent door open 15"), LWC = 0.18 to 0.24 g/cm327 wir0384 40.3 177 0.0 13.75 14.29 90.0 0.6389 43 67.3 44 67 80 21:10 12 Nozzle #11 off , IRT air on ( south vent door open 15"), LWC = 0.10 to 0.14 g/cm328 wir0385 39.6 177 0.0 13.75 14.29 95.0 0.1098 4.5 41.0 4 39 80 21:16 92 All Nozzles on , IRT air on ( south vent door open 15"), LWC = 0.22 to 0.28 g/cm3

NASA/TM—2002-211700 393
Date : August 25, 1997 Note:

AVERAGE PBAR : 13.83 psia 1. Test Model : NACA 64A008DYE CONCENTRATION : 0.0003 grams/cc 2. Pressure data was taken by IRT's ESP system (#2296 ~~ #2314)PSYCHROMETER READINGS : 3. Pressure paint tests was conducted; see Tim Benscic's image

: files and IRT's ESP record #2296 ~~ #2300 and #2310 ~~ #2314

** the Whatman strip was ripped off and ruined the VG100 strip

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION DISK DISPLAY TANK TIME REMARKS

PRESSURE READING PRESSURE

RUN Run I.D. Air TAS IRT P∞ PRESS Humidity PAIR PAIR PWATER PAIR PWATER SPRAY CLOCK MVD ** Only static temperature is recorded

NO. TEMP. (MPH) A.O.A. (psia) TOTAL % PWATER Display Display Gauge Gauge TIME TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) (deg) (psia) (psig) (psig) (psig) (psig) (sec) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0386 46.1 176 0.0 13.83 14.37 75.7 0.2988 22.8 76.3 22 74 6 21:04 22 Nozzle #11 off, IRT air off (vent doors closed)2 wir0387 43.6 176 0.0 13.83 14.37 75.1 0.2902 22.2 76.5 22 74 6 21:24 22 Nozzle #11 off, IRT air on (one Whatman 3MM paper is placed perpendicular on the leading edge) **3 wir0388 45.4 176 0.0 13.84 14.37 71.5 0.2924 22.4 76.6 22 74 6 21:40 22 Nozzle #11 off, IRT air on 4 wir0389 45.1 174 0.0 13.84 14.37 65.4 0.296 22.7 76.7 22 74 6 22:07 22 Nozzle #11 off, IRT air on (pre-spray for 5 minutes)5 wir0390 44.1 176 8.0 13.83 14.37 84.4 0.299 22.9 76.6 22 74 6 22:25 22 Nozzle #11 off, IRT air on (pre-spray for 5 minutes), 46x57 cm sheet Whatman 3MM paper used6 wir0391 45.1 178 8.0 13.82 14.37 71.0 0.2803 21.5 76.7 22 74 6 22:57 22 Nozzle #11 off, IRT air on (pre-spray for 5 minutes), 46x57 cm sheet Whatman 3MM paper used

NASA/TM—2002-211700 394
Date : August 26, 1997 Note:

AVERAGE PBAR : 13.80 psia 1. Test Model: NACA 64A008DYE CONCENTRATION : 0.0003 grams/cc 2. Curved strips were used; Verigood 100 paper onlyPSYCHROMETER READINGS : 3. Strip position: AA is 36" above the floor, BB is 44"

: 4. Gurney Flap was attached on Run #416 and #417

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION DISK DISPLAY TANK TIME REMARKS

PRESSURE READING PRESSURE

RUN Run I.D. Air TAS IRT P∞ PRESS Humidity PAIR PAIR PWATER PAIR PWATER SPRAY CLOCK MVD

NO. TEMP. (MPH) A.O.A. (PSIA) TOTAL % PWATER Display Display Gauge Gauge TIME TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) (deg) (psia) (psig) (psig) (psig) (psig) (sec) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0392 46 175 0.0 13.8 14.33 82.2 0.6455 43.7 67.7 44 67 18 17:25 12 Nozzle #11 off, IRT air on2 wir0393 44.8 177 0.0 13.79 14.33 77.2 0.6411 43.4 67.7 44 67 18 17:40 12 Nozzle #11 off, IRT air on (south vent door open 10")3 wir0394 44.0 176 0.0 13.8 14.34 77.6 0.6435 43.5 67.6 44 67 18 17:50 12 Nozzle #11 off, IRT air on (south vent door open 10")4 wir0395 44.4 176 0.0 13.8 14.33 76.9 0.6401 43.4 67.8 44 67 18 18:01 12 Nozzle #11 off, IRT air on (south vent door open 10")5 wir0396 44.9 175 +6.0 13.8 14.33 76.5 0.6411 43.4 67.7 44 67 18 18:13 12 Nozzle #11 off, IRT air on (south vent door open 10")6 wir0397 44.3 175 +6.0 13.79 14.33 79.6 0.6435 43.5 67.6 44 67 18 13:24 12 Nozzle #11 off, IRT air on (south vent door open 11"), Ttotal = 49.8oF 7 wir0398 46.6 176 +6.0 13.8 14.33 76.2 0.6425 43.5 67.7 44 67 18 18:34 12 Nozzle #11 off, IRT air on (south vent door open 11"), Ttotal = 52.1oF 8 wir0399 43.3 176 +6.0 13.8 14.33 78.5 0.6436 43.7 67.9 44 67 18 18:41 12 Nozzle #11 off, IRT air on (south vent door open 11"), Ttotal = 49.0oF 9 wir0400 43.5 177 +6.0 13.81 14.33 76.0 0.2904 22.3 76.8 22 74 6 18:58 22 Nozzle #11 off, IRT air on (south vent door open 20"), Ttotal = 49.1oF 

10 wir0401 43.3 176 +6.0 13.8 14.33 81.5 0.293 22.5 76.8 22 74 6 19:07 22 Nozzle #11 off, IRT air on (south vent door open 20"), Ttotal = 49.1oF 11 wir0402 45.5 176 +6.0 13.79 14.32 76.5 0.295 22.6 76.6 22 74 6 19:15 22 Nozzle #11 off, IRT air on (south vent door open 16"), Ttotal = 50.9oF 12 wir0403 47.2 176 +6.0 13.8 14.33 74.6 0.2907 22.3 76.7 22 74 6 19:22 22 Nozzle #11 off, IRT air on (south vent door open 16"), Ttotal = 52.9oF 13 wir0404 46.6 176 0.0 13.79 14.33 74.7 0.292 22.4 76.7 22 74 6 19:33 22 Nozzle #11 off, IRT air on (south vent door open 16"), Ttotal = 52.5oF 14 wir0405 42.6 176 0.0 13.79 14.33 81.3 0.2928 22.4 76.5 22 74 6 19:42 22 Nozzle #11 off, IRT air on (south vent door open 16"), Ttotal = 49.9oF 15 wir0406 44.6 176 0.0 13.8 14.33 76.2 0.2928 22.4 76.5 22 74 6 19:51 22 Nozzle #11 off, IRT air on (south vent door open 16"), Ttotal = 50.0oF 16 wir0407 46.6 175 0.0 13.79 14.33 73.7 0.2917 22.4 76.8 22 74 6 20:00 22 Nozzle #11 off, IRT air on (south vent door open 21"), Ttotal = 52.0oF 17 wir0408 42.8 176 0.0 13.78 14.33 80.2 0.1103 4.5 40.8 4 39 3 20:15 92 All Nozzles on, IRT air on (south vent door open 23"), Ttotal = 48.4oF18 wir0409 45.1 177 0.0 13.81 14.33 76.1 0.1054 4.3 40.8 4 39 3 20:23 92 All Nozzles on, IRT air on (south vent door open 23"), Ttotal = 50.7oF19 wir0410 44.3 177 0.0 13.79 14.33 76.5 0.1051 4.3 40.9 4 39 3 20:37 92 All Nozzles on, IRT air on (vent doors closed ), Ttotal = 50.1oF20 wir0411 39.6 176 0.0 13.79 14.33 75.0 0.1125 4.6 40.9 4 39 3 20:49 92 All Nozzles on, IRT air on (vent doors closed), Ttotal = 45.9oF21 wir0412 45.1 175 +6.0 13.79 14.33 73.7 0.11 4.5 40.9 4 39 3 21:12 92 All Nozzles on, IRT air on (south vent door open 13"), Ttotal = 50.4oF22 wir0413 41.7 176 +6.0 13.8 14.34 76.7 0.1029 4.2 40.8 4 39 3 21:23 92 All Nozzles on, IRT air on (vent doors closed), Ttotal = 47.5oF23 wir0414 46.2 177 +6.0 13.81 14.34 78.5 0.1088 4.45 40.9 4 39 3 21:41 92 All Nozzles on, IRT air on (south vent door open 19"), Ttotal = 51.8oF24 wir0415 45.8 176 +6.0 13.8 14.33 77.5 0.1076 4.4 40.9 4 39 3 21:54 92 All Nozzles on, IRT air on (vent doors closed), Ttotal = 51.2oF25 wir0416 44.7 177 +6.0 13.8 14.33 73.5 0.1074 4.4 40.95 4 39 3 22:09 92 All Nozzles on, IRT air on (south vent door open 14"), Ttotal = 49.5oF; Gurney Flap attached26 wir0417 40.5 176 0.0 13.78 14.33 80.4 0.1054 4.3 40.8 4 39 3 22:17 92 All Nozzles on, IRT air on (south vent door open 14"), Ttotal = 46.0oF; Gurney Flap attached

NASA/TM—2002-211700 395
Date : August 27, 1997 Note:

AVERAGE PBAR : 13.80 psia 1. Test Model: MS 317DYE CONCENTRATION : 0.0003 grams/cc 2. wir0442 and wir0443 were impingment observation test -- stripsPSYCHROMETER READINGS : were placed near the trailing edge of the airfoil

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION DISK DISPLAY TANK TIME REMARKS

PRESSURE READING PRESSURE

RUN Run I.D. Air TAS IRT P∞ PRESS Humidity PAIR PAIR PWATER PAIR PWATER SPRAY CLOCK MVD

NO. TEMP. (MPH) A.O.A. (PSIA) TOTAL % PWATER Display Display Gauge Gauge TIME TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) (deg) (psia) (psig) (psig) (psig) (psig) (sec) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0418 43.4 175 0.0 13.73 14.26 82.4 0.6436 43.7 67.9 44 67 18 17:19 12 Nozzle #11 off, IRT air on (south vent door open 11"); Ttotal = 48.3oF2 wir0419 43.1 175 0.0 13.73 14.26 78.9 0.6436 43.7 67.9 44 67 18 17:27 12 Nozzle #11 off, IRT air on (south vent door open 4"); Ttotal = 49.1oF3 wir0420 43.8 177 0.0 13.73 14.26 76.4 0.6406 43.5 67.9 44 67 18 17:38 12 Nozzle #11 off, IRT air on (south vent door open 11"); Ttotal = 49.3oF4 wir0421 43.1 175 0.0 13.74 14.27 76.0 0.6421 43.6 67.9 44 67 18 17:47 12 Nozzle #11 off, IRT air on (vent doors closed); Ttotal = 48.4oF5 wir0422 43.1 175 8.0 13.73 14.26 74.8 0.6441 43.8 68.0 44 67 18 17:56 12 Nozzle #11 off, IRT air on (south vent door open 4"); Ttotal = 48.4oF6 wir0423 42.9 176 8.0 13.74 14.26 75.5 0.6421 43.6 67.9 44 67 18 18:03 12 Nozzle #11 off, IRT air on (south vent door open 4"); Ttotal = 48.8oF7 wir0424 42.4 175 8.0 13.73 14.26 76.0 0.6425 43.5 67.7 44 67 18 18:10 12 Nozzle #11 off, IRT air on (south vent door open 4"); Ttotal = 48.4oF8 wir0425 42.5 175 8.0 13.74 14.26 75.0 0.6401 43.4 67.8 44 67 18 18:17 12 Nozzle #11 off, IRT air on (south vent door open 4"); Ttotal = 48.1oF9 wir0426 45.2 175 8.0 13.74 14.26 73.3 0.2963 22.7 76.6 22 74 6 18:31 22 Nozzle #11 off, IRT air on (south vent door open 5"); Ttotal = 50.5oF

10 wir0427 43.6 176 8.0 13.73 14.26 79.0 0.296 22.7 76.7 22 74 6 18:40 22 Nozzle #11 off, IRT air on (south vent door open 6"); Ttotal = 49.1oF11 wir0428 45.7 176 8.0 13.72 14.26 70.0 0.2917 22.4 76.8 22 74 6 18:56 22 Nozzle #11 off, IRT air on (south vent door open 4"); Ttotal = 51.3oF12 wir0429 47.5 176 8.0 13.74 14.26 73.0 0.2952 22.7 76.9 22 74 6 19:10 22 Nozzle #11 off, IRT air on (vent doors closed); Ttotal = 53.1oF13 wir0430 43.2 175 0.0 13.74 14.26 77.0 0.2947 22.6 76.7 22 74 6 19:17 22 Nozzle #11 off, IRT air on (vent doors closed); Ttotal = 48.7oF14 wir0431 46.4 176 0.0 13.72 14.26 75.2 0.293 22.5 76.8 22 74 6 19:28 22 Nozzle #11 off, IRT air on (south vent door open 14"); Ttotal = 51.8oF15 wir0432 45.8 176 0.0 13.72 14.26 78.3 0.2943 22.6 76.8 22 74 6 19:34 22 Nozzle #11 off, IRT air on (south vent door open 14"); Ttotal = 51.3oF16 wir0433 45.7 177 0.0 13.71 14.25 78.5 0.2999 23 76.7 22 74 6 19:41 22 Nozzle #11 off, IRT air on (south vent door open 14"); Ttotal = 51.3oF17 wir0434 44.2 177 0.0 13.72 14.26 70.5 0.1086 4.4 40.5 4 39 3 20:15 92 All Nozzles on, IRT air on (vent doors closed); Ttotal = 50.0oF18 wir0435 43.6 176 0.0 13.72 14.26 74.4 0.1086 4.4 40.5 4 39 3 20:28 92 All Nozzles on, IRT air on (south vent door open 12"); Ttotal = 49.5oF19 wir0436 43.5 176 0.0 13.72 14.26 78.0 0.1086 4.4 40.5 4 39 3 20:36 92 All Nozzles on, IRT air on (south vent door open 12"); Ttotal = 48.9oF20 wir0437 43.5 176 0.0 13.72 14.26 75.9 0.106 4.3 40.75 4 39 3 20:42 92 All Nozzles on, IRT air on (south vent door open 12"); Ttotal = 49.4oF21 wir0438 43.6 177 8.0 13.72 14.26 75.2 0.1076 4.4 40.9 4 39 3 20:57 92 All Nozzles on, IRT air on (south vent door open 10"); Ttotal = 49.4oF22 wir0439 42.4 177 8.0 13.72 14.26 71.7 0.1051 4.3 40.9 4 39 3 21:06 92 All Nozzles on, IRT air on (vent doors closed); Ttotal = 48.3oF23 wir0440 42.4 177 8.0 13.73 14.26 75.8 0.1076 4.4 40.9 4 39 3 21:18 92 All Nozzles on, IRT air on (vent doors closed); Ttotal = 47.8oF24 wir0441 42.1 176 8.0 13.73 14.26 75.0 0.1098 4.5 41 4 39 3 21:26 92 All Nozzles on, IRT air on (south vent door open 4"); Ttotal = 48.1oF25 wir0442 47.6 176 0.0 13.71 14.25 75.7 0.2924 22.4 76.6 22 74 360 19:50 22 Nozzle #11 off, IRT air on (south vent door open 14"); Ttotal = 53.1oF 26 wir0443 43.7 177 0.0 13.73 14.27 67.5 0.295 22.65 76.77 22 74 360 22:06 22 Nozzle #11 off, IRT air on (south vent door open 4"); Ttotal = 49.0oF 

NASA/TM—2002-211700 396
Date : September 2, 1997 Note:

AVERAGE PBAR : 13.847 psia 1. Test Model: McDonnell Douglas 3 Element AirfoilDYE CONCENTRATION : 0.0003 grams/cc 2. Pressure data were taken by IRT's ESP system (#2324 ~~ #2328)PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION DISK DISPLAY TANK TIME REMARKS

PRESSURE READING PRESSURE

RUN Run I.D. Air TAS IRT P∞ PRESS Humidity PAIR PAIR PWATER PAIR PWATER SPRAY CLOCK MVD

NO. TEMP. (MPH) A.O.A. (PSIA) TOTAL % PWATER Display Display Gauge Gauge TIME TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) (deg) (psia) (psig) (psig) (psig) (psig) (sec) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0444 40.2 176 0.0 13.83 14.38 78.0 0.6398 43.7 68.3 44 67 18 19:40 12 All Nozzles on, IRT ari on (vent doors closed), Ttotal = 45.5oF2 wir0445 40.2 176 0.0 13.82 14.37 77.2 0.6346 42.9 67.6 44 67 18 19:57 12 Nozzle #11 off, IRT ari on (vent doors closed), Ttotal = 44.6oF3 wir0446 39.3 176 0.0 13.84 14.38 77.2 0.6425 43.5 67.7 44 67 18 20:13 12 Nozzle #11 off, IRT ari on (vent doors closed), Ttotal = 44.6oF4 wir0447 39.9 176 0.0 13.84 14.38 75.9 0.6475 43.9 67.8 44 67 18 20:33 12 All Nozzles on, IRT ari on (south vent door open 6"), Ttotal = 45.3oF5 wir0448 43.6 175 0.0 13.84 14.37 70.5 0.6445 43.7 67.8 44 67 18 20:50 12 Nozzle #11 off, IRT ari on (vent doors closed), Ttotal = 49.0oF6 wir0449 43.0 175 0.0 13.85 14.38 73.0 0.6426 43.7 68.0 44 67 18 21:06 12 Nozzle #11 off, IRT ari on (vent doors closed), Ttotal = 48.5oF7 wir0450 37.5 175 4.0 13.85 14.39 76.0 0.6451 43.8 67.9 44 67 18 21:25 12 Nozzle #11 off, IRT ari on (vent doors closed ), Ttotal = 42.5oF8 wir0451 38.1 174 4.0 13.85 14.4 77.2 0.644 43.6 67.7 44 67 18 21:36 12 Nozzle #11 off, IRT ari on (vent doors closed), Ttotal = 43.9oF9 wir0452 39.8 175 4.0 13.86 14.4 76.0 0.6426 43.7 68.0 44 67 18 21:46 12 Nozzle #11 off, IRT ari on (vent doors closed), Ttotal = 45.5oF

10 wir0453 40.4 174 4.0 13.86 14.39 73.0 0.6412 43.6 68.0 44 67 18 21:56 12 Nozzle #11 off, IRT ari on (vent doors closed), Ttotal = 45.9oF11 wir0454 41.5 174 4.0 13.87 14.4 77.2 0.2945 22.5 76.4 22 74 6 22:10 22 Nozzle #11 off, IRT ari on (south vent door open 14", and then closed before spray), Ttotal = 47.2oF12 wir0455 39.3 176 4.0 13.85 14.4 76.0 0.2937 22.5 76.6 22 74 6 22:21 22 Nozzle #11 off, IRT ari on (vent doors closed), Ttotal = 44.9oF13 wir0456 40.3 177 4.0 13.85 14.4 74.7 0.3095 23.8 76.9 22 74 6 22:30 22 Nozzle #11 off, IRT ari on (vent doors closed), Ttotal = 45.8oF14 wir0457 42.0 175 4.0 13.85 14.4 72.5 0.2937 22.5 76.6 22 74 6 22:41 22 Nozzle #11 off, IRT ari on (south vent door opened 14", and the closed before spray), Ttotal = 47.3oF15 wir0458 41.2 178 0.0 13.85 14.4 75.5 0.2934 22.5 76.7 22 74 6 22:57 22 Nozzle #11 off, IRT ari on (vent doors closed), Ttotal = 46.7oF

NASA/TM—2002-211700 397
Date : September 3, 1997 Note:

AVERAGE PBAR : 13.886 psia 1. Test Model: McDonnell Douglas 3 Element AirfoilDYE CONCENTRATION : 0.0003 grams/cc 2. Tim10 ~~ Tim15 were flow visualization tests (Tim Bencic)PSYCHROMETER READINGS : 3. wir0471 ~~ wir0472 were special tests for simulating the frost in

: wind tunnel

4. Pressure data was taken by IRT's ESP system (#2338 ~~ #2355)*** The gap between slat and main element was sealed  Gaps between slat, main element, and flap were sealed** *** The gap between main element and flap was sealed

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION DISK DISPLAY TANK TIME REMARKS

PRESSURE READING PRESSURE

RUN Run I.D. Air TAS IRT P∞ PRESS Humidity PAIR PAIR PWATER PAIR PWATER SPRAY CLOCK MVD

NO. TEMP. (MPH) A.O.A. (PSIA) TOTAL % PWATER Display Display Gauge Gauge TIME TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) (deg) (psia) (psig) (psig) (psig) (psig) (sec) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0459 41.7 177 0.0 13.88 14.43 78.5 0.292 22.39 76.7 22 74 6 15:10 22 Nozzle #11 off, IRT air on, (south vent door open 15"), Ttotal = 47.5oF2 Tim10 39.3 174 -4.0 13.89 14.43 74.8 0.2906 22.23 76.5 22 74 20 15:35 22 Nozzle #11 off, IRT air on, (south vent door open 15"), Ttotal = 45.0oF, image filename: am4.pmi3 Tim11 38.5 174 0.0 13.89 14.43 78.9 0.2926 22.44 76.7 22 74 20 15:38 22 Nozzle #11 off, IRT air on, (south vent door open 15"), Ttotal = 44.1oF, image filename: a00.pmi4 Tim12 40.1 176 +4.0 13.9 14.43 76.4 0.2918 22.37 76.7 22 74 20 15:40 22 Nozzle #11 off, IRT air on, (south vent door open 15"), Ttotal = 46.0oF, image filename: ap4.pmi5 Tim13 38.4 175 +8.0 13.91 14.43 78.6 0.2905 22.3 76.8 22 74 20 15:43 22 Nozzle #11 off, IRT air on, (south vent door open 15"), Ttotal = 43.7oF, image filename: ap8.pmi6 Tim14 39.0 175 +10.0 13.89 14.43 76.1 0.2924 22.4 76.6 22 74 20 15:46 22 Nozzle #11 off, IRT air on, (vent doors closed), Ttotal = 44.9oF, image filename: ap10.pmi7 Tim15 40.1 175 +6.0 13.89 14.43 68.9 0.2928 22.43 76.6 22 74 20 15:48 22 Nozzle #11 off, IRT air on, (south vent door open 10"), Ttotal = 45.5oF, image filename: ap6.pmi8 wir0460 38.7 176 0.0 13.9 14.43 75.8 0.2926 22.5 76.9 22 74 6 16:06 22 Nozzle #11 off, IRT air on, (south vent door open 27"), Ttotal = 44.3oF9 wir0461 37.7 174 0.0 13.88 14.42 80.5 0.2913 22.4 76.9 22 74 6 16:20 22 Nozzle #11 off, IRT air on, (south vent door open 31"), Ttotal = 43.0oF

10 wir0462 38.1 174 0.0 13.88 14.42 76.5 0.2887 22.2 76.9 22 74 6 16:29 22 Nozzle #11 off, IRT air on, (south vent door open 31"), Ttotal = 44.1oF11 wir0463 39.2 174 0.0 13.88 14.42 71.5 0.1076 4.4 40.9 4 39 3 16:43 92 All Nozzles on, IRT air on, (south vent door open 29"), Ttotal = 45.0oF12 wir0464 38.0 175 0.0 13.88 14.42 75.0 0.1078 4.4 40.8 4 39 3 16:55 92 All Nozzles on, IRT air on, (vent doors closed), Ttotal = 43.5oF13 wir0465 38.7 175 0.0 13.88 14.43 76.0 0.11 4.5 40.9 4 39 3 17:07 92 All Nozzles on, IRT air on, (south vent door open 29", and then closed before spraying), Ttotal = 43.8oF14 wir0466 40.0 176 0.0 13.88 14.42 71,5 0.11 4.5 40.9 4 39 3 17:31 92 All Nozzles on, IRT air on, (south vent 31" & north vent 30"), Ttotal = 45.8oF15 wir0467 38.7 176 +4.0 13.87 14.42 76.2 0.1083 4.46 41.2 4 39 3 19:07 92 All Nozzles on, IRT air on, (south vent 31" & north vent 30"), Ttotal = 44.2oF16 wir0468 38.0 176 +4.0 13.88 14.42 72.0 0.1067 4.36 40.9 4 39 3 19:30 92 All Nozzles on, IRT air on, (south vent 31" & north vent 30"), Ttotal = 43.7oF17 wir0469 40.7 174 +4.0 13.89 14.42 72.0 0.1074 4.4 41.0 4 39 3 19:46 92 All Nozzles on, IRT air on, (south vent 31" & north vent 30"), Ttotal = 43.6oF, 50% steam @ turning vein18 wir0470 38.2 174 +4.0 13.88 14.43 70.0 0.1038 4.3 40.9 4 39 3 19:57 92 All Nozzles on, IRT air on, (south vent 31" & north vent 30"), Ttotal = 44.6oF, 50% steam @ turning vein19 wir0471 38.1 177 0.0 13.88 14.43 81.0 0.3005 22.9 76.2 22 74 360 20:28 22 Nozzle #11 off, IRT air on, (vent doors closed), Ttotal = 43.7oF, 50% steam @ turning vein20 wir0472 42.9 178 0.0 13.88 14.43 68 ~ 73 0.2849 21.9 76.9 22 74 360 21:08 22 Nozzle #11 off, IRT air off, (vent doors closed), Ttotal = 48.3oF21 wir0473 37.9 177 0.0 13.88 14.44 72.2 0.295 22.6 76.6 22 74 6 21:36 22 Nozzle #11 off, IRT air on, (vent doors closed), Ttotal = 43.7oF ***22 wir0474 37.1 175 0.0 13.9 14.44 76.5 0.2939 22.6 76.9 22 74 6 21:54 22 Nozzle #11 off, IRT air on, (vent doors closed), Ttotal = 42.6oF  23 wir0475 40.4 175 0.0 13.9 14.44 72.0 0.29 22.3 76.9 22 74 6 22:09 22 Nozzle #11 off, IRT air on, (vent doors closed), Ttotal = 42.6oF ** ***

NASA/TM—2002-211700 398
Date : September 4, 1997 Note:

AVERAGE PBAR : 13.869 psia 1. Test Model: Collector Mechanism (wir0476 ~~ wir0488) andDYE CONCENTRATION : 0.0003 grams/cc Uniformity Grid (wir0489 ~~ wir0491)PSYCHROMETER READINGS : 2. wir0492 ~~ wir0500 were for calibration curves

: 2. Hot Steam was supplied during the spray to increase the

 humidity. (aft test section)3. Hot steam (50%) also installed on the turning vein (east end)** Strips on all the blades. The capital letters (A, B, C, .....) on the  strips were pointing outwards

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION DISK DISPLAY TANK TIME REMARKS

PRESSURE READING PRESSURE

RUN Run I.D. Air TAS IRT P∞ PRESS Humidity PAIR PAIR PWATER PAIR PWATER SPRAY CLOCK MVD

NO. TEMP. (MPH) A.O.A. (PSIA) TOTAL % PWATER Display Display Gauge Gauge TIME TIME ** IRT 80 lbs air when tunnel was in operating condition

(oF) (deg) (psia) (psig) (psig) (psig) (psig) (sec) ** IRT 20 lbs air when tunnel was in idle condition

1 wir0476 38.6 175 0.0 13.88 14.42 77.5 0.6426 43.7 68.0 44 67 18 17:19 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 44.5oF2 wir0477 41.6 176 0.0 13.91 14.42 73.1 0.6416 43.5 67.8 44 67 18 17:38 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 47.3oF3 wir0478 40.2 177 0.0 13.86 14.41 77.9 0.6392 43.4 67.9 44 67 18 17:46 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 46.2oF4 wir0479 33.9 174 0.0 13.88 14.42 80.0 0.6435 43.5 67.6 44 67 18 17:58 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 39.6oF ** (high humidity)5 wir0480 41.2 173 0.0 13.88 14.41 67 ~ 76 0.651 44.2 67.9 44 67 18 18:13 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 47.3oF ** (no hot steam aft test section)6 wir0481 41.4 176 0.0 13.87 14.41 73.6 0.3103 23.8 76.7 22 74 6 18:29 22 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 46.9oF7 wir0482 39.9 174 0.0 13.87 14.41 75.9 0.3304 22.4 67.8 22 74 6 18:35 22 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 45.7oF8 wir0483 37.8 176 0.0 13.87 14.41 75 ~ 78 0.2961 22.8 77.0 22 74 6 18:42 22 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 43.4oF 9 wir0484 41.1 176 0.0 13.87 14.41 71.7 0.2956 22.7 76.8 22 74 6 18:49 22 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 47.4oF **

10 wir0485 34.9 175 0.0 13.88 14.41 77 ~ 79 0.1155 4.7 40.7 4 39 3 19:00 92 All Nozzles on, IRT air on (vent doors closed), Ttotal = 40.8oF 11 wir0486 38.6 176 0.0 13.86 14.41 77.1 0.1149 4.7 40.9 4 39 3 19:08 92 All Nozzles on, IRT air on (vent doors closed), Ttotal = 44.8oF 12 wir0487 37.9 176 0.0 13.87 14.41 78.5 0.1125 4.6 40.9 4 39 3 19:13 92 All Nozzles on, IRT air on (vent doors closed), Ttotal = 43.1oF 13 wir0488 38.7 174 0.0 13.86 14.41 72.0 0.1146 4.7 41.0 4 39 3 19:21 92 All Nozzles on, IRT air on (vent doors closed), Ttotal = 44.3oF **14 wir0489 39.4 175 0.0 13.85 14.4 72.5 0.1091 4.45 40.8 4 39 3 20:28 92 All Nozzles on, IRT air on (vent doors closed), Ttotal = 44.1oF 15 wir0490 40.7 175 0.0 13.86 14.41 78.0 0.6413 43.8 68.3 44 67 18 20:43 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 46.7oF 16 wir0491 38.4 175 0.0 13.87 14.41 78.2 0.2922 22.5 77.0 22 74 6 20:56 22 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 44.4oF 17 wir0492 37.8 175 0.0 13.87 14.41 78.0 0.3382 23.0 68.0 44 67 2 21:08 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 43.7oF ; air pressure not right !!18 wir0493 38.6 175 0.0 13.87 14.41 78.0 0.4412 30.0 68.0 44 67 20 21:15 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 44.1oF ; air pressure not right !!19 wir0494 40.8 175 0.0 13.86 14.42 69.0 0.647 43.8 67.7 44 67 4 21:22 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 44.6oF 20 wir0495 35.1 176 0.0 13.86 14.41 75.7 0.6441 43.8 68.0 44 67 18 21:29 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 40.4oF 21 wir0496 37.2 175 0.0 13.86 14.41 75.0 0.6422 43.8 68.2 44 67 6 21:35 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 40.2oF 22 wir0497 40.0 175 0.0 13.87 14.41 76.3 0.6422 43.8 68.2 44 67 16 21:40 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 42.6oF 23 wir0498 42.0 175 0.0 13.88 14.41 75.2 0.6402 43.6 68.1 44 67 1 21:46 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 45.4oF 24 wir0499 37.6 175 0.0 13.87 14.41 79.3 0.6402 43.6 68.1 44 67 8 21:51 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 43.4oF 25 wir0500 39.7 175 0.0 13.87 14.41 74.0 0.6402 43.6 68.1 44 67 10 21:57 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 45.1oF 26 wir0501 35.4 175 0.0 13.87 14.41 77.9 0.6393 43.6 68.2 44 67 12 22:02 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 41.0oF 27 wir0502 36.9 176 0.0 13.86 14.41 78.5 0.6435 43.5 67.6 44 67 14 22:06 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 42.2oF 28 wir0503 39.3 176 0.0 13.86 14.41 72.5 0.6454 43.5 67.4 44 67 2 22:13 12 Nozzle #11 off, IRT air on (vent doors closed), Ttotal = 44.8oF 

NASA/TM—2002-211700 399

Date : February 2, 1999

PBAR :

DYE CONCENTRATION : No dye Note:

PSYCHROMETER READING

S : Uniformity Tests.

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

1 R001 44.9 176 13.77 14.2 39.4 77.6 60 7:00 12 IRT air 80 psi, vent door close, steam on, nozzle #11 off.

2 R002 47.9 176 13.76 14.2 42.4 76.2 0.2897 3.2 11.2 60 7:05 12 IRT air off, vent door close, steam on, nozzle #11 off.3 R003 48.5 175 13.82 14.2 43.2 69.5 0.1510 3.2 21.0 60 7:09 12 IRT air 80 psi, vent door close, steam on, all nozzles.4 R004 47.7 176 13.78 14.3 42 67.7 0.1030 3.2 31.0 60 7:10 12 IRT air off, vent door close, steam on, all nozzles.5 R005 48.2 176 13.84 14.2 42.7 66.5 0.0813 3.4 41.4 22 77 60 7:22 21 IRT air 80 psi, vent door close, steam on, nozzle #11 off.6 R006 49.6 176 13.76 14.3 44.1 69.9 0.0615 3.1 51.1 22 77 30 7:25 21 IRT air off, vent door close, steam on, nozzle #11 off.7 R007 51.6 175 13.78 14.3 46.2 73.9 0.0531 3.2 61.0 22 77 30 7:28 21 IRT air 80 psi, vent door close, steam on, all nozzles.8 R008 51 176 13.81 14.3 45.7 66.4 0.0449 3.2 70.7 22 77 25 7:32 21 IRT air off, vent door close, steam on, all nozzles.9 R009 47.7 173 13.84 14.2 42.2 71.4 0.0407 3.3 80.6 25 7:37 92 IRT air 80 psi, vent door close, steam on, nozzle #11 off.

10 R010 49 176 13.77 14.3 43.3 71.8 0.0678 4.9 71.9 25 7:39 92 IRT air off, vent door close, steam on, nozzle #11 off.11 R011 50.1 174 13.79 14.2 44.7 70.9 0.1012 7.3 72.0 25 7:42 92 IRT air 80 psi, vent door close, steam on, all nozzles.12 R012 51.1 176 13.75 14.2 45.4 70.4 0.1644 11.8 71.9 25 7:44 92 IRT air off, vent door close, steam on, all nozzles.13 R013 52.1 175 13.84 14.3 46.6 69.2 0.2250 16.2 71.8 22 77 25 7:48 21 IRT air 80 psi, vent door close, steam on, nozzle #1 only.14 R014 52.6 176 13.77 14.2 47.2 70.6 0.2944 20.8 70.8 22 77 25 7:50 21 IRT air off, vent door close, steam on, nozzle #1 only.15 R015 49.5 175 13.83 14.3 44.1 63.8 0.2885 20.7 71.8 22 77 25 7:54 21 IRT air 80 psi, vent door close, steam on, nozzle #2 only.16 R016 49.8 177 13.82 14.2 44.2 64.4 0.3559 25.5 71.6 22 77 25 7:56 21 IRT air off, vent door close, steam on, nozzle #2 only.17 R017 50.3 175 13.8 14.3 44.8 63.6 0.4148 29.7 71.6 22 77 25 7:58 21 IRT air 80 psi, vent door close, steam on, nozzle #3 only.18 R018 50.8 177 13.79 14.3 45.4 62.9 0.4813 34.4 71.6 22 77 25 8:04 21 IRT air off, vent door close, steam on, nozzle #3 only.

bad R019 50.5 177 13.78 14.2 44.9 63.8 22 77 25 8:15 21 IRT air off, vent door close, steam on, nozzle #4 only.

19 R019 51.4 177 13.82 14.2 45.8 63.9 0.5444 39.0 71.7 22 77 25 8:18 21 IRT air off, vent door close, steam on, nozzle #4 only.20 R020 49.2 177 13.79 14.3 43.8 61.1 0.6073 43.4 71.5 22 77 25 8:21 21 IRT air off, vent door close, steam on, nozzle #5 only.21 R021 47 177 13.75 14.3 41.4 64.4 0.6732 48.3 71.7 22 77 25 8:25 21 IRT air off, vent door close, steam on, nozzle #6 only.22 R022 48.3 177 13.75 14.3 42.7 65.4 0.7350 52.8 71.8 22 77 25 8:28 21 IRT air off, vent door close, steam on, nozzle #7 only.23 R023 49.6 177 13.8 14.2 44.1 64.9 0.7266 52.1 71.7 22 77 25 8:30 21 IRT air off, vent door close, steam on, nozzle #8 only.24 R024 50.5 177 13.76 14.2 44.9 64.9 0.6935 44.3 63.9 22 77 25 8:33 21 IRT air off, vent door close, steam on, nozzle #9 only.25 R025 51.3 177 13.84 14.2 45.6 65.2 0.6764 43.5 64.4 22 77 25 8:35 21 IRT air off, vent door close, steam on, nozzle #10 only.26 R026 52 177 13.78 14.2 46.4 67 0.3411 24.4 71.5 22 77 25 8:37 21 IRT air off, vent door close, steam on, nozzle #11 only.27 R027 50.2 177 13.82 14.3 44.7 62.6 0.1985 7.5 37.6 22 77 25 8:39 21 IRT air off, vent door close, steam on, nozzle #12 only.28 R028 49.7 175 13.83 14.2 44.2 63 0.3405 24.4 71.6 22 77 25 8:44 21 IRT air 80 psi, vent door close, steam on, nozzle #4 only.29 R029 48.8 176 13.79 14.2 43.4 67.8 0.6753 43.6 64.5 22 77 25 8:46 21 IRT air 80 psi, vent door close, steam on, nozzle #5 only.30 R030 49.3 176 13.76 14.3 43.7 78.4 0.1980 7.4 37.2 22 77 25 9:06 21 IRT air 80 psi, vent door close, steam on, nozzle #6 only.31 R031 50.8 175 13.83 14.3 45.3 76.8 0.6753 43.5 64.4 22 77 25 9:08 21 IRT air 80 psi, vent door close, steam on, nozzle #7 only.32 R032 52.2 176 13.85 14.3 46.6 76.3 0.1977 7.4 37.2 22 77 25 9:11 21 IRT air 80 psi, vent door close, steam on, nozzle #8 only.33 R033 53.1 175 13.85 14.2 47.6 76.7 0.3364 24.2 71.9 22 77 25 9:15 21 IRT air 80 psi, vent door close, steam on, nozzle #9 only.34 R034 54.1 176 13.76 14.2 48.6 77.4 22 77 25 9:16 21 IRT air 80 psi, vent door close, steam on, nozzle #10 only.35 R035 51.5 176 13.81 14.3 46 67.7 22 77 25 9:20 21 IRT air 80 psi, vent door close, steam on, nozzle #11 only.36 R036 51 176 13.8 14.2 45.5 67.7 22 77 25 9:23 21 IRT air 80 psi, vent door close, steam on, nozzle #12 only.

NASA/TM—2002-211700 401

Appendix E: Run Log for 1999 Impingement Tests
Date : February 3, 1999

PBAR :

DYE CONCENTRATION : No dye Note:

PSYCHROMETER READINGS : Uniformity Tests.

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

37 R037 57.2 177 13.76 14.3 51.6 57.3 0.3352 24.0 71.7 22 77 30 5:55 21 nozzle #4 moved, all nozzles spray, IRT air off, steam on.

38 R038 52.3 176 13.78 14.2 46.8 62.4 0.3351 24.1 72.0 22 77 30 7:13 21 nozzle #7 moved, all nozzles spray, IRT air off, steam on.39 R039 53.8 176 13.8 14.2 48.2 68.4 0.3395 24.5 72.0 22 77 30 8:28 21 nozzle #2 moved, all nozzles spray, IRT air off, steam on.40 R040 51 176 13.77 14.3 45.5 59.4 0.6694 43.5 64.9 43 67 30 8:39 11 nozzle #2 moved, all nozzles spray, IRT air off, steam on.41 R041 53.6 176 13.75 14.3 47.9 65 0.2047 7.7 37.8 30 8:47 92 nozzle #2 moved, all nozzles spray, IRT air off, steam on.42 R042 51.8 176 13.77 14.3 46.1 62 0.2051 7.7 37.7 30 8:52 92 nozzle #2 moved, IRT air off, steam on, nozzle #11 off.43 R043 51.8 176 13.81 14.2 46.3 60.1 0.2015 7.7 38.2 30 9:00 92 nozzles #7, 8, 9 and 10 only. IRT air off, steam on.44 R044 50.9 176 13.76 14.3 45.2 62.1 0.1966 7.5 38.2 30 9:03 92 nozzles #1, 6, 11 and 12 only. IRT air off, steam on.45 R045 52.2 176 13.84 14.2 46.6 63.1 0.1873 7.2 38.3 30 9:06 92 nozzles #2, 3, 4 and 5 only. IRT air off, steam on.46 R046 53.4 176 13.78 14.3 47.7 64.2 0.1968 7.6 38.4 30 9:10 92 nozzles #6, 7, 8 and 11 only. IRT air off, steam on.47 R047 49.9 177 13.82 14.3 44.3 58.3 0.2024 7.6 37.6 30 9:50 92 all nozzles, with nozzle at 6 and 10 switched with each other, IRT air off, steam on.48 R048 52.4 177 13.84 14.3 46.7 47.1 0.1946 7.4 37.8 30 10:07 92 nozzle #12 off, IRT air off, steam on.49 R049 53.1 178 13.77 14.2 47.5 44 0.1920 7.3 37.9 30 10:13 92 repeat of run #48

NASA/TM—2002-211700 402
Date : February 4, 1999 (cont.)

PBAR :

DYE CONCENTRATION : (refer to note 2) Note:

PSYCHROMETER READINGS : 1. Uniformity Tests.

: 2. No dye in sect. 1 (3:45pm - 5:00pm), but water for runs in

 sect. 2 (7:10pm - 8:50pm) and 3 (9:00pm - 10:30pm) has dye.

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

50 R050 all nozzles. Nozzles #8 and #12 moved.

51 R051 46.2 176 13.76 14.2 40.6 82.2 0.1958 7.2 36.6 30 3:55 92 IRT air off, steam on. All nozzles. Nozzles #8 and #12 moved. (repeat of run #50)52 R052 52.4 175 13.75 14.2 46.9 72.8 0.2026 7.7 37.8 30 4:09 92 IRT air off, steam on. All nozzles. Nozzles #6 "modified".53 R053 55.3 176 13.8 14.2 50 89.5 0.3320 24.0 72.4 22 77 30 4:14 21 same as run #5254 R054 56.4 175 13.77 14.3 48 85.4 0.3382 24.3 71.9 22 77 30 4:15 21 same as run #5355 R055 54.1 176 13.85 14.2 48.6 87.4 0.6673 43.3 64.9 43 67 30 4:18 11 same as run #5456 R056 53 176 13.76 14.2 47.4 61.6 0.6690 43.4 64.9 43 67 30 4:20 11 same as run #5557 R057 54.5 175 13.77 14.3 48.9 63.8 0.3272 24.0 73.4 22 77 30 4:27 21 nozzle #1 only, IRT air off, steam on.58 R058 53.7 176 13.81 14.3 48.4 59.8 0.3298 24.1 73.0 22 77 30 4:29 21 nozzle #2 only, IRT air off, steam on.59 R059 52.5 175 13.78 14.2 47 59.2 0.3305 24.1 72.8 22 77 30 4:31 21 nozzle #3 only, IRT air off, steam on.60 R060 53.1 176 13.77 14.3 47.7 61.4 0.3298 24.1 73.0 22 77 30 4:33 21 nozzle #4 only, IRT air off, steam on.61 R061 54.2 175 13.76 14.2 48.7 61.8 0.3291 24.0 73.0 22 77 30 4:35 21 nozzle #5 only, IRT air off, steam on.62 R062 53.5 176 13.77 14.2 48.1 57.5 0.3294 24.1 73.2 22 77 30 4:37 21 nozzle #6 only, IRT air off, steam on.63 R063 53.5 175 13.83 14.3 48 58 0.3281 24.1 73.4 22 77 30 4:39 21 nozzle #7 only, IRT air off, steam on.64 R064 53.4 176 13.79 14.2 48 57.5 0.3289 24.1 73.3 22 77 30 4:41 21 nozzle #8 only, IRT air off, steam on.65 R065 51.7 175 13.82 14.3 46.2 57 0.3306 24.1 72.9 22 77 30 4:43 21 nozzle #9 only, IRT air off, steam on.66 R066 52.2 176 13.8 14.2 48.6 58.3 0.3293 24.1 73.1 22 77 30 4:44 21 nozzle #10 only, IRT air off, steam on.67 R067 53.2 175 13.81 14.3 47.6 80.5 0.3305 24.1 73.0 22 77 30 4:46 21 nozzle #11 only, IRT air off, steam on.68 R068 54.1 176 13.78 14.3 48.6 81.6 0.3291 24.1 73.2 22 77 30 4:48 21 nozzle #12 only, IRT air off, steam on.69 R069 52.7 176 13.8 14.2 47.3 58.7 0.3316 24.2 73.1 22 77 30 4:50 21 nozzle #7, 8, 9, 10 and 12, IRT air off, steam on.70 R070 52.4 176 13.82 14.2 46.8 81.3 0.3303 24.0 72.6 22 77 30 4:52 21 nozzle #1, 5, 6 and 11, IRT air off, steam on.71 R071 53.2 176 13.79 14.3 47.7 82.9 0.3328 24.2 72.7 22 77 30 4:55 21 nozzle #2, 3, 4 and 5, IRT air off, steam on.72 R072 54.3 176 13.75 14.3 48.7 63.1 0.3292 24.0 72.9 22 77 30 4:57 21 nozzle #7, 8 and 12, IRT air off, steam on.73 R073 47.2 175 13.77 14.3 41.8 74 0.6677 43.4 65.0 43 67 18 7:23 11 uniformity with grids: (3,3), (3,4), (3,5), (2,4), and (4,4), steam on, IRT air off.74 R074 47.6 175 13.8 14.2 42 73.3 0.6673 43.3 64.9 43 67 16 7:31 11 same as above.75 R075 49.5 175 13.75 14.3 44.1 77.8 0.6670 43.4 65.1 43 67 14 7:38 11 same as above.76 R076 53.6 175 13.84 14.2 48 76.9 0.6692 43.4 64.9 43 67 12 7:49 11 same as above.77 R077 53.8 175 13.78 14.2 48.3 75.4 0.6684 43.3 64.8 43 67 10 7:58 11 same as above.78 R078 54.4 175 13.83 14.3 48.6 73.6 0.3361 24.2 71.9 22 77 6 8:04 21 same as above.79 R079 54.7 175 13.82 14.2 48.2 71.4 0.3353 24.1 71.9 22 77 5 8:10 21 same as above.80 R080 48.7 177 13.78 14.2 43 69.3 0.3351 24.2 72.1 22 77 4 8:39 21 same as above.81 R081 48.7 177 13.8 14.3 43.8 70.4 0.2016 7.6 37.9 3 8:46 92 same as above.82 R082 50.3 177 13.81 14.3 44.7 70.8 0.2007 7.6 37.7 2.5 8:51 92 same as above.

NASA/TM—2002-211700 403
Date : February 4, 1999

PBAR :

DYE CONCENTRATION : (refer to note 2) Note:

PSYCHROMETER READINGS : 1. Uniformity Tests.

: 2. No dye in sect. 1 (3:45pm - 5:00pm), but water for runs in

 sect. 2 (7:10pm - 8:50pm) and 3 (9:00pm - 10:30pm) has dye.

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

83 R083 48.2 174 13.82 14.3 42.7 64.4 0.3345 24.2 72.3 22 77 30 9:14 21 nozzle #1 off, IRT air off, steam off.

84 R084 47.6 175 13.83 14.2 42.2 66.5 0.3345 24.1 72.2 22 77 30 9:17 21 nozzle #2 off, IRT air off, steam off.85 R085 48.3 175 13.77 14.2 42.8 69.8 0.3334 24.1 72.3 22 77 30 9:19 21 nozzle #3 off, IRT air off, steam off.86 R086 49.4 175 13.76 14.3 43.9 71.9 0.3328 24.1 72.5 22 77 30 9:21 21 nozzle #4 off, IRT air off, steam off.87 R087 50.4 175 13.8 14.2 44.9 73.2 0.3344 24.1 72.2 22 77 30 9:23 21 nozzle #5 off, IRT air off, steam off.88 R088 50.1 175 13.8 14.2 44.7 69.1 0.3336 24.1 72.2 22 77 30 9:25 21 nozzle #6 off, IRT air off, steam off.89 R089 48 175 13.79 14.3 43.7 68.3 0.3344 24.1 72.2 22 77 30 9:27 21 nozzle #7 off, IRT air off, steam off.90 R090 48.1 175 13.75 14.3 43.6 68.4 0.3328 24.1 72.4 22 77 25 9:28 21 nozzle #8 off, IRT air off, steam off.91 R091 49.5 175 13.77 14.3 44 69.5 0.3343 24.1 72.2 22 77 25 9:29 21 nozzle #9 off, IRT air off, steam off.92 R092 50.1 175 13.8 14.2 44.6 68.9 0.3346 24.1 72.2 22 77 25 9:31 21 nozzle #10 off, IRT air off, steam off.93 R093 50.6 175 13.77 14.3 45.1 70.1 0.3347 24.2 72.2 22 77 25 9:33 21 nozzle #11 off, IRT air off, steam off.94 R094 51.1 174 13.82 14.2 45.7 70.2 0.3352 24.2 72.1 22 77 25 9:35 21 nozzle #12 off, IRT air off, steam off.95 R095 49.4 176 13.78 14.2 43.9 67 0.3335 24.1 72.3 22 77 25 9:37 21 all nozzles, IRT air 80 psi, steam off.96 R096 49.1 176 13.82 14.3 43.5 68.4 0.1977 7.5 37.7 25 9:41 92 same as above.97 R097 48.9 176 13.8 14.2 44.5 67.5 0.6704 43.5 64.8 43 67 25 9:44 11 same as above.98 R098 50.7 176 13.79 14.2 45.1 66.7 0.6676 43.4 65.0 43 67 25 9:46 11 all nozzles, IRT air 60 psi, steam off.99 R099 51.2 176 13.78 14.2 45.7 66 0.3361 24.2 72.1 22 77 25 9:48 21 same as above.

100 R100 48 176 13.78 14.2 43.6 66.1 0.1992 7.5 37.6 25 9:51 92 same as above.101 R101 48.7 175 13.8 14.2 43.2 66 0.1979 7.5 37.8 25 9:53 92 all nozzles, IRT air 40 psi, steam off.102 R102 49.4 176 13.79 14.3 44 66 0.3358 24.2 72.1 22 77 25 9:55 21 all nozzles, IRT air 40 psi, steam off.103 R103 50.1 175 13.76 14.2 44.6 67.4 0.6694 43.4 64.8 43 67 25 9:57 11 same as above.104 R104 50.2 175 13.76 14.3 44.7 66.7 0.6692 43.4 64.9 43 67 25 9:59 11 all nozzles, IRT air 20 psi, steam off.105 R105 47.8 176 13.78 14.2 42.4 64.8 0.3348 24.2 72.2 22 77 25 10:01 21 same as above.106 R106 48 176 13.76 14.2 42.5 66.7 0.2019 7.6 37.6 25 10:03 92 same as above.107 R107 49.2 174 13.8 14.2 44.3 66.6 0.3290 24.0 73.0 22 77 25 10:07 21 nozzle #2 and #10, IRT air off, steam off.108 R108 50.4 175 13.78 14.3 44.8 66.8 0.3306 24.1 72.8 22 77 25 10:10 21 nozzle #1, #3 and #9, IRT air off, steam off.109 R109 50.8 175 13.82 14.3 45.4 67 0.3303 24.0 72.7 22 77 25 10:13 21 nozzle #4, #5, #8 and #11, IRT air off, steam off.110 R110 48.7 176 13.83 14.2 43.3 66 0.3308 24.1 72.7 22 77 25 10:15 21 nozzle #4, #5, #7 and #12, IRT air off, steam off.111 R111 48.7 175 13.76 14.2 43.2 68.8 0.3297 24.0 72.9 22 77 25 10:17 21 nozzle #2, and #3, IRT air off, steam off.112 R112 49.3 176 13.76 14.3 43.9 68.8 0.3297 24.0 72.9 22 77 25 10:20 21 nozzle #1, #4 and #10 IRT air off, steam off.113 R113 50.2 175 13.83 14.3 44.6 68 0.3296 24.0 72.8 22 77 25 10:22 21 nozzle #5, #9 and #11, IRT air off, steam off.114 R114 50.6 176 13.84 14.3 45.1 67.3 0.3299 24.0 72.9 22 77 25 10:23 21 nozzle #6, #7 and #12, IRT air off, steam off.115 R115 48.7 176 13.79 14.3 43.3 66.7 0.3307 24.1 72.8 22 77 25 10:26 21 nozzle #2, #5, #7 and #10, IRT air off, steam off.116 R116 49 176 13.8 14.2 43.5 69.3 0.3307 24.0 72.7 22 77 25 10:28 21 nozzle #3, #4, #6, #9, and #12, IRT air off, steam off.117 R117 49.5 175 13.76 14.2 44 68 0.3296 24.0 73.0 22 77 25 10:30 21 nozzle #1, #8 and #11, IRT air off, steam off.

NASA/TM—2002-211700 404
Date : February 5, 1999 (cont.)

PBAR :

DYE CONCENTRATION : blue dye 0.0003 gram/cc Note:

PSYCHROMETER READINGS : 1. Uniformity Tests.

: 2.Test starts at about 2:00pm.

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

118 R118 49.8 171 13.75 14.3 44.5 73.2 22 77 25 1:43 21 all nozzles, steam on, IRT air off.

119 R119 52.6 170 13.77 14.3 47.4 55.7 0.3270 23.9 73.1 22 77 25 2:39 21 nozzle #1 only, steam on, IRT air off.120 R120 53.6 171 13.82 14.3 48.6 56.1 0.3281 24.0 73.1 22 77 25 2:40 21 nozzle #2 only, steam on, IRT air off.121 R121 52.3 171 13.76 14.3 47.4 53.8 0.3288 24.0 73.1 22 77 25 2:42 21 nozzle #3 only, steam on, IRT air off.122 R122 51.4 171 13.78 14.2 46.2 52.7 0.3282 24.0 73.1 22 77 25 2:44 21 nozzle #7 only, steam on, IRT air off.123 R123 51.6 171 13.77 14.3 46.6 55 0.3278 24.0 73.1 22 77 25 2:46 21 nozzle #8 only, steam on, IRT air off.124 R124 52.8 171 13.8 14.2 47.5 55.5 0.3286 24.0 73.1 22 77 25 2:48 21 nozzle #9 only, steam on, IRT air off.125 R125 53.6 171 13.76 14.3 48.4 55.5 0.3288 24.0 73.0 22 77 25 2:49 21 nozzle #10 only, steam on, IRT air off.126 R126 52.4 171 13.84 14.2 47.4 53.3 0.3285 24.0 73.0 22 77 25 2:51 21 nozzle #12 only, steam on, IRT air off.127 R127 51.4 170 13.75 14.2 46.2 53.8 0.3321 24.1 72.6 22 77 25 2:54 21 nozzle #1, 2, 3, 7, 8, 9, 10 and 12. Steam on, IRT air off.128 R128 55.9 176 13.81 14.3 50.3 76.6 0.3295 24.1 73.1 22 77 25 4:11 21 nozzle #2, 5, 7, 8 and 10 after nozzle #10 was moved. Steam on, IRT air off.129 R129 50.3 176 13.84 14.2 44.7 77.2 0.3336 24.2 72.5 22 77 25 4:20 21 all nozzles, IRT air off, steam on. 130 R130 52.9 176 13.78 14.3 47.4 72.4 0.3329 24.2 72.6 22 77 25 4:24 21 all nozzles, IRT air 80 psi, steam on. 131 R131 53.7 176 13.79 14.2 48.2 64.6 0.1972 7.4 37.8 25 4:29 92 all nozzles, IRT air off, steam on. 132 R132 53.4 175 13.78 14.2 48 64.2 0.6643 43.4 65.4 43 67 25 4:34 11 all nozzles, IRT air off, steam on. 133 R133 50.2 176 13.78 14.2 44.7 69.6 0.6533 43.4 66.5 43 67 25 4:51 11 same as above.134 R134 51.5 177 13.8 14.2 46 69.8 0.6629 43.4 65.4 43 67 25 4:55 11 same as above.135 R135 52.8 176 13.79 14.3 47.2 73.3 0.3335 24.2 72.4 22 77 25 5:55 21 all nozzles, after nozzle #10 moved, steam on, IRT air off.136 R136 52 176 13.76 14.2 46.4 71 0.3335 24.2 72.5 22 77 25 5:57 21 repeat run #135137 R137 52.9 176 13.79 14.3 47.3 70.5 0.1976 7.5 37.9 25 6:00 92 same as run #135138 R138 53.8 177 13.78 14.3 48.3 69.6 0.6650 43.3 65.2 43 67 25 6:03 11 same as run #135139 R139 50.8 176 13.76 14.2 45.3 71 0.3335 24.1 72.4 22 77 25 7:13 21 nozzle #2 off, IRT air off, steam off.140 R140 52.3 176 13.82 14.2 46.7 69.1 0.3323 24.1 72.5 22 77 25 7:15 21 nozzle #1 off, IRT air off, steam off.141 R141 53.4 177 13.77 14.3 47.8 69.2 0.3326 24.1 72.5 22 77 25 7:17 21 nozzle #3 off, IRT air off, steam off.142 R142 54.4 177 13.82 14.3 48.8 69.4 0.3325 24.2 72.7 22 77 25 7:19 21 nozzle #4 off, IRT air off, steam off.

NASA/TM—2002-211700 405
Date : February 5, 1999

PBAR :

DYE CONCENTRATION : blue dye 0.0003 gram/cc Note:

PSYCHROMETER READINGS : 1. Uniformity Tests.

: 2.Test starts at about 2:00pm.

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

143 R143 51.4 177 13.83 14.2 46.1 62.9 0.3329 24.2 72.6 22 77 25 7:21 21 nozzle #5 off, IRT air off, steam off.

144 R144 50.4 176 13.79 14.2 44.9 67.1 0.3326 24.1 72.6 22 77 25 7:25 21 nozzle #6 off, IRT air off, steam on.145 R145 51.7 177 13.76 14.3 46.2 68.2 0.3324 24.1 72.5 22 77 25 7:27 21 nozzle #7 off, IRT air off, steam on.146 R146 52.7 176 13.85 14.2 47.1 38.3 0.3326 24.1 72.5 22 77 25 7:28 21 nozzle #8 off, IRT air off, steam on.147 R147 53.5 177 13.84 14.3 47.9 68.5 0.3330 24.1 72.4 22 77 25 7:32 21 nozzle #9 off, IRT air off, steam on.148 R148 53.9 176 13.79 14.3 48.5 67.1 0.3320 24.1 72.7 22 77 25 7:34 21 nozzle #10 off, IRT air off, steam on.149 R149 53.2 176 13.8 14.3 47.6 63.5 0.3323 24.1 72.6 22 77 25 7:36 21 nozzle #11 off, IRT air off, steam on.150 R150 53.1 177 13.76 14.2 47.5 64.4 0.3330 24.2 72.5 22 77 25 7:38 21 nozzle #12 off, IRT air off, steam on.151 R151 52.1 176 13.77 14.3 46.6 60.5 0.3270 24.0 73.4 22 77 25 7:43 21 nozzle #2 only, IRT air off, steam on.152 R152 52.1 177 13.85 14.2 46.5 62.2 0.3269 24.0 73.4 22 77 25 7:45 21 nozzle #4 only, IRT air off, steam on.153 R153 52.5 177 13.76 14.2 47 62.4 0.3275 24.0 73.3 22 77 25 7:47 21 nozzle #5 only, IRT air off, steam on.154 R154 53.3 176 13.78 14.3 47.8 62.6 0.3272 24.0 73.2 22 77 25 7:49 21 nozzle #6 only, IRT air off, steam on.155 R155 53.9 176 13.81 14.3 48.4 63.1 0.3280 24.0 73.2 22 77 25 7:50 21 nozzle #11 only, IRT air off, steam on.156 R156 52.9 176 13.8 14.2 47.5 72.9 0.3331 24.2 72.5 22 77 25 8:57 21 all nozzles, IRT air off, steam on, nozzle #2 moved.157 R157 53.8 177 13.75 14.3 48.3 74.5 0.3268 24.0 73.4 22 77 25 8:59 21 nozzle #2 only, IRT air off, steam on.158 R158 52.2 177 13.78 14.2 46.6 64.4 0.3341 24.2 72.4 22 77 25 9:14 21 all nozzles, IRT air off, steam on (repeat run #156)159 R159 53 176 13.77 14.2 47.4 65.4 0.3325 24.1 72.6 22 77 25 9:16 21 nozzle #2 off, IRT air off, steam on.160 R160 52.2 177 13.81 14.3 46.7 61.6 0.3271 24.0 73.4 22 77 25 9:19 21 nozzle #2 only, IRT air off, steam on.161 R161 52.2 177 13.79 14.2 46.5 62.7 0.3349 24.2 72.4 22 77 25 9:39 21 all nozzles, IRT air off, steam on. 162 R162 52.9 176 13.82 14.3 47.2 63.4 0.3338 24.2 72.4 22 77 25 9:41 21 repeat of run #161163 R163 52 176 13.8 14.2 46.5 61.4 0.1963 7.5 38.1 25 9:47 92 same as of run #161164 R164 50.8 176 13.81 14.3 45.2 62.3 0.1979 7.5 38.0 25 9:49 92 same as of run #161165 R165 51.9 176 13.77 14.3 46.3 75.5 0.6639 43.4 65.4 43 67 25 10:05 11 same as of run #161166 R166 52.3 175 13.79 14.2 47.1 71.4 0.6626 43.3 65.3 43 67 25 10:12 11 same as of run #161167 R167 47.3 175 13.77 14.2 41.7 74.5 0.3342 24.1 72.2 22 77 4.5 10:35 21 IRT air off, steam on, all nozzles, uniformity grids.168 R168 48.7 175 13.83 14.3 43.3 75.6 0.1999 7.6 38.1 2.5 10:53 92 IRT air off, steam on, all nozzles, uniformity grids.

NASA/TM—2002-211700 406
Date : February 8, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc Note:

PSYCHROMETER READINGS : Uniformity Tests and King's Probe

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

169 R169 45.1 176 13.82 14.3 39.7 73.1 0.6666 39.5 59.3 43 67 10 7:05 11 IRT air off, steam on, all nozzles, uniformity grid.

170 R170 46 176 13.84 14.2 40.5 75 0.6626 39.3 59.4 43 67 10 7:22 11 IRT air off, steam on, all nozzles, uniformity grid.171 R171 47.9 176 13.78 14.2 42.3 72.5 0.3045 20.2 66.2 22 77 4.5 7:32 21 IRT air off, steam on, all nozzles, uniformity grid.172 R172 44.8 175 13.8 14.3 39.3 70.1 0.1150 3.7 32.1 3 7:52 92 IRT air off, steam on, all nozzles, uniformity grid.173 R173 47.1 176 13.76 14.3 41.6 71.7 0.1184 3.8 32.2 1 8:02 92 IRT air off, steam on, all nozzles, uniformity grid, only one grid point (4,2).174 R174 46 175 13.79 14.3 40.4 65.7 0.1140 3.7 32.7 1.5 8:26 92 IRT air off, steam on, all nozzles, uniformity grid, only one grid point (4,2).175 R175 45.8 175 13.82 14.2 40.3 69.2 0.1241 4.0 32.3 2 8:33 92 IRT air off, steam on, all nozzles, uniformity grid, only one grid point (4,2).176 R176 45.7 175 13.78 14.3 40.2 72.9 0.1189 3.7 31.5 2.5 8:37 92 IRT air off, steam on, all nozzles, uniformity grid, only one grid point (4,2).177 R177 46 51 13.81 14.2 45.5 74.4 0.1088 3.5 32.0 2.5 8:49 92 Spash test with 1" square located at (3,3), (3,4) and (3,5) of uniformity grid; all nozzles, IRT air off, steam on.178 R178 44 100 13.8 14.3 42.3 71.2 0.1197 3.9 32.2 2.5 8:56 92 Spash test with 1" square located at (3,3), (3,4) and (3,5) of uniformity grid; all nozzles, IRT air off, steam on.179 R179 44 153 13.79 14.3 39.8 72.4 0.1223 3.9 31.9 2.5 9:02 92 Spash test with 1" square located at (3,3), (3,4) and (3,5) of uniformity grid; all nozzles, IRT air off, steam on.180 R180 45.5 200 13.77 14.3 38.3 75.2 0.1263 4.1 32.3 2.5 9:07 92 Spash test with 1" square located at (3,3), (3,4) and (3,5) of uniformity grid; all nozzles, IRT air off, steam on.181 R181 48.2 200 13.78 14.2 41 70.3 0.1173 3.8 32.1 2.5 9:14 92 Spash test with one collector strip; all nozzles, IRT air off, steam on.182 R182 44.7 151 13.8 14.2 40.7 72.7 0.1240 3.9 31.8 2.5 9:21 92 Spash test with one collector strip; all nozzles, IRT air off, steam on.183 R183 43.9 100 13.79 14.3 42.2 71.3 0.1206 3.9 32.2 2.5 9:27 92 Spash test with one collector strip; all nozzles, IRT air off, steam on.184 R184 43.5 50 13.76 14.3 43.1 70.9 0.1159 3.7 32.0 2.5 9:32 92 Spash test with one collector strip; all nozzles, IRT air off, steam on.185 R185 45.5 176 13.76 14.3 40.1 69.8 0.6632 39.4 59.4 43 67 60 10:44 11 King's probe; all nozzles, steam on, IRT air off.186 R186 46.2 176 13.8 14.2 40.8 71.7 0.6630 39.4 59.5 43 67 60 10:47 11 Repeat of run #185187 R187 45 176 13.77 14.3 39.6 69 0.3049 20.2 66.4 22 77 60 10:50 21 King's probe; all nozzles, steam on, IRT air off.188 R188 44.7 176 13.8 14.2 39.1 75.8 0.3021 20.2 66.9 22 77 60 10:53 21 Repeat of run #186189 R189 45.5 176 13.75 14.3 40.1 71.8 0.3055 20.3 66.4 22 77 4.5 10:58 21 King's probe; all nozzles, steam on, IRT air off.190 R190 46.6 176 13.77 14.2 41.1 72.8 0.1150 3.7 32.0 60 11:00 92 King's probe; all nozzles, steam on, IRT air off.191 R191 46.8 176 13.82 14.2 41.3 71.3 0.1121 3.6 31.9 2.5 11:02 92 King's probe; all nozzles, steam on, IRT air off.

NASA/TM—2002-211700 407
Date : February 10, 1999 (cont.)

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS Humidity Humidity TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) % % Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (start) (end) (oF) (PM)

224 R224 53.4 177 59.7 47.9 0.3080 9.9 32.1 6 37 60 5:09 94 all nozzles, IRT air off, steam on, King and laser. King is 36" above tunnel floor.

225 R225 50.7 176 55.9 45.2 0.3159 10.1 32.1 6 37 60 5:12 94 repeat of run #224226 R226 46.5 175 65.1 65.4 41 0.3067 9.8 31.9 6 37 3 5:15 94 all nozzles, IRT air off, steam on, King and laser. King is 36" above tunnel floor227 R227 48.9 176 64.9 64.5 43.4 0.3070 9.9 32.3 6 37 3 5:18 94 repeat of run #226228 R228 46.5 175 61.2 65.5 41.4 0.2700 19.6 72.6 22 77 60 5:21 21 all nozzles, IRT air off, steam on, King and laser. King is 36" above tunnel floor229 R229 46.3 176 68.3 70.5 40.7 0.2674 19.3 72.3 22 77 60 5:25 21 repeat of run #228230 R230 47.2 176 65.8 64.7 41.6 0.2667 19.3 72.4 22 77 4.5 5:28 21 all nozzles, IRT air off, steam on, King and laser. King is 36" above tunnel floor231 R231 47 176 63.8 64 41.4 0.2673 19.3 72.3 22 77 4.5 5:29 21 repeat of run #230232 R232 47.4 176 63.2 63.1 41.8 0.5084 31.6 62.1 43 67 60 5:33 11 all nozzles, IRT air off, steam on, King and laser. King is 36" above tunnel floor233 R233 46.6 176 63.4 65.8 41.2 0.5047 31.4 62.2 43 67 60 5:34 11 repeat of run #232

233a R233a 45.2 176 74.4 75.7 39.6 0.5059 31.5 62.4 43 67 60 5:51 11 repeat of run #233

234 R234 46.7 176 66.5 66.2 41.2 0.5042 31.4 62.3 43 67 10 6:01 11 all nozzles, IRT air off, steam on, King and laser. King is 36" above tunnel floor235 R235 46.5 176 67.3 67.5 41 0.5044 31.4 62.2 43 67 10 6:03 11 repeat of run #234236 R236 46.9 176 66.3 65.2 41.5 0.3120 10.0 32.1 6 37 60 6:17 94 all nozzles, IRT air off, steam on, King and laser. King is 42" above tunnel floor237 R237 46.8 176 67.9 69.3 41.4 0.3111 10.0 32.2 6 37 60 6:21 94 repeat of run #236238 R238 45 176 70.5 72.5 39.3 0.2704 19.5 72.3 22 77 60 6:30 21 all nozzles, IRT air off, steam on, King and laser. King is 42" above tunnel floor239 R239 46.8 176 72.6 74.6 41.2 0.2697 19.5 72.4 22 77 60 6:32 21 all nozzles, IRT air off, steam on, King and laser. King is 42" above tunnel floor240 R240 46.4 176 65.7 71.1 40.5 0.5097 31.9 62.5 43 67 60 6:36 11 all nozzles, IRT air off, steam on, King and laser. King is 42" above tunnel floor241 R241 43.7 176 75.7 77.1 38.2 0.5104 31.7 62.1 43 67 60 6:40 11 repeat of run #240

241a R241a 46.1 176 75.6 76.7 40.7 0.5038 31.4 62.3 43 67 60 6:45 11 repeat of run #241

242 R242 46.9 176 71.4 72.8 41.4 0.3130 10.0 32.1 6 37 60 6:55 94 all nozzles, IRT air off, steam on, King and laser. King is 30" above tunnel floor243 R243 45 176 68 70 39.5 0.3150 10.0 31.9 6 37 60 6:59 94 repeat of run #242244 R244 47.5 176 72.6 74.7 42 0.2718 19.6 72.2 22 77 60 7:07 21 all nozzles, IRT air off, steam on, King and laser. King is 30" above tunnel floor245 R245 45.7 176 68.8 72.3 40.1 0.2728 19.7 72.2 22 77 60 7:13 21 repeat of run #244246 R246 46.9 176 72.1 73.4 41.3 0.5108 31.7 62.1 43 67 60 7:17 11 all nozzles, IRT air off, steam on, King and laser. King is 30" above tunnel floor247 R247 48 176 73.4 74.7 42.4 0.5080 31.5 62.1 43 67 60 7:19 11 repeat of run #246

NASA/TM—2002-211700 408
Date : February 10, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS Humidity Humidity TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) % % Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (start) (end) (oF) (PM)

248 R248 45.5 175 54.9 55.8 40 0.3227 10.2 31.6 6 37 60 8:27 94 Humidity test: RHUM=55, King probe.

249 R249 46.7 175 55.2 56 40.6 0.2663 19.3 72.4 22 77 60 8:31 21 Humidity test: RHUM=55, King probe.250 R250 46.9 176 55.2 55.7 41.4 0.5059 31.4 62.0 43 67 60 8:34 11 Humidity test: RHUM=55, King probe.251 R251 46.4 176 58.7 60.6 41.1 0.3110 9.9 31.9 6 37 60 8:41 94 Humidity test: RHUM=60, King probe.252 R252 46 176 59.5 60.3 40.5 0.2714 19.6 72.2 22 77 60 8:44 21 Humidity test: RHUM=60, King probe.253 R253 47 176 59.7 60.3 41.4 0.5083 31.5 62.0 43 67 60 8:47 11 Humidity test: RHUM=60, King probe.254 R254 47.4 174 67.4 68.2 41.9 0.5069 31.4 62.0 43 67 60 9:09 11 Humidity test: RHUM=65, King probe.255 R255 49.3 174 64.5 66.6 43.9 0.2685 19.4 72.1 22 77 60 9:15 21 Humidity test: RHUM=65, King probe.256 R256 47.7 175 65.3 65.9 42.3 0.3136 10.0 31.8 6 37 60 9:20 94 Humidity test: RHUM=65, King probe.257 R257 48 174 75.6 73.9 42.7 0.5060 31.5 62.2 43 67 60 9:29 11 Humidity test: RHUM=75, King probe.258 R258 47 176 72.9 73.7 41.5 0.2722 19.6 72.1 22 77 60 9:32 21 Humidity test: RHUM=75, King probe.259 R259 47.1 176 76.7 76 41.6 0.3185 10.2 31.9 6 37 60 9:35 94 Humidity test: RHUM=75, King probe.260 R260 46.2 177 85.2 85 40.6 0.5132 31.8 61.9 43 67 60 9:44 11 Humidity test: RHUM=85, King probe.261 R261 47.9 176 86.3 85.8 42.4 0.2703 19.5 72.2 22 77 60 9:47 21 Humidity test: RHUM=85, King probe.262 R262 46.7 175 85.9 85 41.4 0.3232 10.2 31.6 6 37 60 9:55 94 Humidity test: RHUM=85, King probe.263 R263 45.4 50 77.5 78.2 45 0.2209 7.0 31.5 6 37 30 10:57 94 Refill water tank. Need to multiply LWC from King probe by 120/43, all nozzles, steam on, IRT air off.264 R264 44.8 100 75 74.5 43.1 0.2634 8.4 31.8 6 37 30 11:00 94 Need to multiply LWC from King probe by 120/89, all nozzles, steam on, IRT air off.265 R265 45 150 73.9 75.1 41 0.2978 9.5 31.9 6 37 30 11:02 94 all nozzles, steam on, IRT air off, King probe.266 R266 48 200 74.1 74.7 40.7 0.3337 10.7 32.1 6 37 30 11:06 94 all nozzles, steam on, IRT air off, King probe.

NASA/TM—2002-211700 409
Date : February 11, 1999 (cont.)

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

267 R267 53.5 175 48 56.6 0.6082 38.1 62.6 43 67 60 3:56 11 IRT air off, steam on, to take laser image, alpha=0 deg, all nozzles. (MS-317)

268 R268 53.5 175 48.2 59.2 0.6015 37.9 63.1 43 67 60 4:04 11 IRT air off, steam on, to take laser image, alpha=10 deg, all nozzles. (MS-317)269 R269 50.2 176 44.8 64.1 0.2599 18.9 72.9 22 77 60 4:22 21 IRT air off, steam on, to take laser image, alpha=10 deg, all nozzles. (MS-317)270 R270 47.6 176 42.1 63.4 0.2558 18.6 72.7 22 77 60 4:26 21 IRT air off, steam on, to take laser image, alpha=0 deg, all nozzles. (MS-317)271 R271 48.8 175 43.4 65.5 0.1460 4.8 32.8 6 37 60 4:30 94 IRT air off, steam on, to take laser image, alpha=0 deg, all nozzles. (MS-317)272 R272 47 177 41.5 66.8 0.1370 4.4 32.3 6 37 60 4:35 94 IRT air off, steam on, to take laser image, alpha=10 deg, all nozzles. (MS-317)273 R273 47.1 176 41.7 68 0.2497 18.5 74.0 22 77 60 4:42 21 IRT air off, steam on, to take laser image, alpha=10 deg, nozzle #1 only. (MS-317)274 R274 48.3 176 42.7 74.1 0.2545 18.7 73.5 22 77 30 4:44 21 IRT air off, steam on, to take laser image, alpha=10 deg, nozzle #2 only. (MS-317)275 R275 53.4 175 47.7 84 0.2551 18.8 73.8 22 77 30 5:10 21 IRT air off, steam on, to take laser image, alpha=10 deg, nozzle #12 only. (MS-317)276 R276 55.2 176 49.8 82.9 0.2515 18.6 73.8 22 77 20 5:14 21 IRT air off, steam on, to take laser image, alpha=10 deg, nozzle #11 only. (MS-317)277 R277 54.5 175 49.1 74.5 0.2517 18.6 73.7 22 77 20 5:16 21 IRT air off, steam on, to take laser image, alpha=10 deg, nozzle #10 only. (MS-317)278 R278 54.6 175 49.1 73.9 0.2549 18.7 73.5 22 77 20 5:18 21 IRT air off, steam on, to take laser image, alpha=10 deg, nozzle #9 only. (MS-317)279 R279 55 177 49.5 72.2 0.2528 18.6 73.6 22 77 20 5:21 21 IRT air off, steam on, to take laser image, alpha=10 deg, nozzle #8 only. (MS-317)280 R280 55 176 49.6 70.8 0.2527 18.6 73.7 22 77 20 5:23 21 IRT air off, steam on, to take laser image, alpha=10 deg, nozzle #7 only. (MS-317)281 R281 55.2 176 49.7 71.4 0.2539 18.7 73.7 22 77 20 5:24 21 IRT air off, steam on, to take laser image, alpha=10 deg, nozzle #6 only. (MS-317)282 R282 54.8 176 49.3 68.1 0.2550 18.7 73.2 22 77 20 5:25 21 IRT air off, steam on, to take laser image, alpha=10 deg, nozzle #5 only. (MS-317)283 R283 53.3 175 48.1 60.1 0.2536 18.5 73.1 22 77 20 5:26 21 IRT air off, steam on, to take laser image, alpha=10 deg, nozzle #4 only. (MS-317)284 R284 49.8 177 44.2 68.9 0.2552 18.8 73.6 22 77 20 5:29 21 IRT air off, steam on, to take laser image, alpha=10 deg, nozzle #3 only. (MS-317)285 R285 50.6 176 45.1 71.9 0.2547 18.7 73.6 22 77 20 5:32 21 IRT air off, steam on, to take laser image, alpha=0 deg, nozzle #1 only. (MS-317)286 R286 50.9 176 45.3 71.1 0.2555 18.8 73.6 22 77 20 5:33 21 IRT air off, steam on, to take laser image, alpha=0 deg, nozzle #2 only. (MS-317)287 R287 50 175 44.6 66.8 0.2536 18.7 73.6 22 77 20 5:35 21 IRT air off, steam on, to take laser image, alpha=0 deg, nozzle #3 only. (MS-317)288 R288 45.5 176 39.9 70.1 0.2522 18.6 73.7 22 77 20 5:37 21 IRT air off, steam on, to take laser image, alpha=0 deg, nozzle #4 only. (MS-317)289 R289 45.4 176 39.9 75.6 0.2546 18.8 73.7 22 77 20 5:39 21 IRT air off, steam on, to take laser image, alpha=0 deg, nozzle #5 only. (MS-317)290 R290 46 176 40.4 79.1 0.2512 18.5 73.7 22 77 15 5:40 21 IRT air off, steam on, to take laser image, alpha=0 deg, nozzle #6 only. (MS-317)291 R291 46.9 176 41.4 80.9 0.2524 18.6 73.8 22 77 15 5:41 21 IRT air off, steam on, to take laser image, alpha=0 deg, nozzle #7 only. (MS-317)292 R292 48.5 176 42.9 82.3 0.2509 18.5 73.7 22 77 15 5:42 21 IRT air off, steam on, to take laser image, alpha=0 deg, nozzle #8 only. (MS-317)293 R293 49 176 43.5 75.3 0.2482 18.3 73.8 22 77 15 5:44 21 IRT air off, steam on, to take laser image, alpha=0 deg, nozzle #9 only. (MS-317)294 R294 48.5 177 43 70.2 0.2520 18.6 73.8 22 77 15 5:45 21 IRT air off, steam on, to take laser image, alpha=0 deg, nozzle #10 only. (MS-317)295 R295 47.8 176 42.4 66.7 0.2565 18.9 73.8 22 77 15 5:46 21 IRT air off, steam on, to take laser image, alpha=0 deg, nozzle #11 only. (MS-317)296 R296 47.6 176 42.2 67.7 0.2530 18.7 73.7 22 77 15 5:47 21 IRT air off, steam on, to take laser image, alpha=0 deg, nozzle #12 only. (MS-317)

Note: Taking laser image, pressure data were not recorded

NASA/TM—2002-211700 410
Date : February 11, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

297 R297 51.1 175 13.68 14.21 45.6 70.5 0.2569 18.6 72.5 22 77 4.5 6:33 21 IRT air off, steam on, blotter strips A & B, alpha=0 deg, all nozzles. (MS-317)

298 R298 49.8 176 13.68 14.2 44.4 71.3 0.2573 18.7 72.7 22 77 4.5 6:43 21 repeat of run #297.299 R299 50.8 176 13.67 14.2 45.2 73.8 0.2601 18.9 72.6 22 77 4.5 6:50 21 repeat of run #297.300 R300 52.3 177 13.67 14.2 46.8 78.4 0.6074 38.1 62.7 43 67 10 6:57 11 IRT air off, steam on, blotter strips A & B, alpha=0 deg, all nozzles. (MS-317)301 R301 49.3 176 13.68 14.2 44 73.2 0.6026 38.0 63.1 43 67 10 7:04 11 repeat of run #300.302 R302 49.6 175 13.67 14.2 44.1 73.1 0.6037 38.0 63.0 43 67 10 7:11 11 repeat of run #300.303 R303 51.4 176 13.67 14.2 45.7 75.3 0.1476 4.8 32.4 6 37 2.5 7:20 94 IRT air off, steam on, blotter strips A & B, alpha=0 deg, all nozzles. (MS-317)304 R304 52.5 176 13.67 14.13 47 74.2 0.1475 4.8 32.6 6 37 2.5 7:27 94 repeat of run #303.305 R305 50.5 176 13.67 14.2 45 70.6 0.1479 4.8 32.2 6 37 2.5 7:34 94 repeat of run #303.306 R306 52 202 13.51 14.2 44.8 69.8 0.1517 4.9 32.6 6 37 2.5 7:43 94 Splashing test, IRT air off, steam on, alpha=0 deg, only strip A, all nozzles. (MS-317)307 R307 49 151 13.8 14.2 45 71.9 0.1469 4.8 32.4 6 37 2.5 7:49 94 Splashing test, IRT air off, steam on, alpha=0 deg, only strip A, all nozzles. (MS-317)308 R308 49 100 14.01 14.19 47.2 68.9 0.1375 4.4 32.3 6 37 2.5 7:55 94 Splashing test, IRT air off, steam on, alpha=0 deg, only strip A, all nozzles. (MS-317)309 R309 48.9 51 14.15 14.19 48.5 70.2 0.1494 4.8 32.4 6 37 2.5 8:02 94 Splashing test, IRT air off, steam on, alpha=0 deg, only strip A, all nozzles. (MS-317)310 R310 50.3 174 13.67 14.19 45 72.4 0.1392 4.5 32.3 6 37 2.5 8:10 94 IRT air off, steam on, alpha=8 deg, only strip A, all nozzles. (MS-317)311 R311 52.8 177 13.67 14.2 47.3 75.8 0.2605 18.9 72.5 22 77 4.5 8:27 21 IRT air off, steam on, alpha=8 deg, only strip A, all nozzles. (MS-317)312 R312 50.3 174 13.67 14.2 44.9 70.6 0.6051 38.1 63.0 43 67 10 8:39 11 IRT air off, steam on, alpha=8 deg, only strip A, all nozzles. (MS-317)313 R313 50 175 13.67 14.18 44.5 71.1 0.6027 37.9 62.9 43 67 10 9:39 11 Collector mechanism: strips at locations A, C, E, G, and I.alpha=0 deg, all nozzles, IRT air off, steam on.314 R314 52 176 13.66 14.18 46.5 74 0.6089 38.2 62.7 43 67 10 9:47 11 Collector mechanism: I-strip.alpha=0 deg, all nozzles, IRT air off, steam on.315 R315 48.5 176 13.66 14.18 43 76.3 0.2568 18.6 72.5 22 77 4.5 9:57 21 Collector mechanism: strips at locations A, C, E, G, and I.alpha=0 deg, all nozzles, IRT air off, steam on.316 R316 48.5 175 13.66 14.18 43.1 72.8 0.2605 18.9 72.6 22 77 4.5 10:04 21 Collector mechanism: I-strip.alpha=0 deg, all nozzles, IRT air off, steam on.317 R317 49.7 175 13.66 14.18 44.3 70.6 0.1513 4.9 32.7 6 37 2.5 10:15 94 Collector mechanism: strips at locations A, C, E, G, and I.alpha=0 deg, all nozzles, IRT air off, steam on.318 R318 51.9 175 13.65 14.18 46.3 74.8 0.1462 4.7 32.4 6 37 2.5 10:23 94 Collector mechanism: I-strip.alpha=0 deg, all nozzles, IRT air off, steam on.319 R319 51 150 13.79 14.17 47 68.3 0.1398 4.5 32.4 6 37 2.5 10:30 94 Collector mechanism: I-strip.alpha=0 deg, all nozzles, IRT air off, steam on, Splashing test.320 R320 48.9 100 13.99 14.17 47.1 72.3 0.1446 4.7 32.4 6 37 2.5 10:37 94 Collector mechanism: I-strip. Alpha=0 deg, all nozzles, IRT air off, steam on, Splashing test.321 R321 48.7 50 14.12 14.17 48.2 73.3 0.1343 4.4 32.6 6 37 2.5 10:43 94 Collector mechanism: I-strip. Alpha=0 deg, all nozzles, IRT air off, steam on, Splashing test.322 R322 49 174 13.64 14.17 43.6 70.1 0.1372 4.4 32.3 6 37 2 10:50 94 Collector mechanism: I-strip. Alpha=0 deg, all nozzles, IRT air off, steam on, Splashing test.323 R323 51 175 13.64 14.17 45.4 75.4 0.2586 18.8 72.8 22 77 3.5 10:56 21 Collector mechanism: I-strip. Alpha=0 deg, all nozzles, IRT air off, steam on.

NASA/TM—2002-211700 411
Date : February 12, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

324 R324 175 NLF-0414f, 48", delta=0 deg, alpha=-5,-4,-3,...,10,11,12 deg, from rdg #6634 to #6651.

325 R325 140 NLF-0414f, 48", delta=0 deg, alpha=12,8,4,0,-4 deg, from rdg #6652 to #6656.326 R326 85 NLF-0414f, 48", delta=0 deg, alpha=-4,0,4,8,12 deg, from rdg #6657 to #6661.327 R327 175 NLF-0414f, 48", delta=5 deg, alpha=-4,-2,-1,0,1,2,3,4,5 deg, from rdg #6662 to #6670.328 R328 175 NLF-0414f, 48", delta=15 deg, alpha=5,4,3,2,1,0,-1,-2,-4 deg, from rdg #6671 to #6679.329 R329 45.7 175 13.79 14.33 40.2 68.1 0.1481 4.8 32.6 6 37 2.2 9:00 94 all nozzles, IRT air off, steam on, alpha=0 deg, delta=0 deg.330 R330 46 176 13.79 14.33 40.5 69.9 0.1491 4.8 32.2 6 37 2.2 9:08 94 repeat run #329331 R331 46.1 175 13.8 14.34 40.7 67.5 0.1330 4.3 32.7 6 37 2.2 9:17 94 repeat run #329332 R332 43.1 175 13.8 14.33 37.7 71.5 0.1473 4.8 32.4 6 37 2.2 9:24 94 repeat run #329333 R333 46.6 176 13.79 14.33 40.9 74.2 0.6098 38.3 62.8 43 67 9 9:46 11 all nozzles, IRT air off, steam on, alpha=0 deg, delta=0 deg.334 R334 44.8 177 13.77 14.32 39.2 73.5 0.6156 38.5 62.5 43 67 9 9:55 11 repeat run #333335 R335 46.8 176 13.77 14.32 41.3 73.5 0.6159 38.5 62.5 43 67 9 10:07 11 repeat run #333 <NOTE: B-strip tape came off!>336 R336 46.5 177 13.79 14.33 41 72.3 0.6106 38.2 62.6 43 67 9 10:15 11 repeat run #333337 R337 44.9 176 13.79 14.33 39.3 71.9 0.6126 38.4 62.6 43 67 9 10:24 11 all nozzles, IRT air off, steam on, alpha=8 deg, delta=0 deg, B-strip only.338 R338 44.9 177 13.8 14.33 39.4 71.6 0.6078 38.0 62.5 43 67 9 10:30 11 repeat run #337339 R339 45.4 177 13.8 14.33 40 74.6 0.6097 38.1 62.5 43 67 9 10:36 11 repeat run #337

NASA/TM—2002-211700 412
Date : February 13, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

340 R340 46.1 175 14.16 14.71 40.6 76.3 0.6132 38.4 62.7 43 67 9 10:15 11 all nozzles, delta=15 deg, alpha=0 deg, steam on, IRT air off, A&B strips.

341 R341 44.7 177 14.16 14.72 39.1 74.4 0.6004 37.8 63.0 43 67 9 10:37 11 repeat run #340342 R342 47.1 175 14.16 14.72 41.6 70.3 0.6067 38.0 62.7 43 67 9 10:57 11 repeat run #340343 R343 45.3 175 14.17 14.73 39.8 75.4 0.2610 18.9 72.5 22 77 3.8 11:28 21 all nozzles, delta=15 deg, alpha=0 deg, steam on, IRT air off, A&B strips.344 R344 48 175 14.18 14.73 43.8 75 0.2584 18.7 72.5 22 77 3.8 12:02 21 repeat run #343345 R345 43.8 174 14.18 14.73 38.2 75.2 0.2607 18.9 72.3 22 77 3.8 12:21 21 repeat run #343346 R346 43.9 175 14.19 14.74 38.6 74.4 0.2616 19.0 72.5 22 77 3.8 12:30 21 repeat run #343 (B strip only)347 R347 46.6 173 14.18 14.73 41.2 73.8 0.1496 4.8 32.2 6 37 2.2 1:00 94 all nozzles, delta=15 deg, alpha=0 deg, steam on, IRT air off, B strip only.348 R348 47.7 175 14.19 14.74 42.2 72.4 0.1393 4.5 32.3 6 37 2.2 2:00 94 repeat run #347349 R349 46.3 176 14.18 14.74 40.7 70 0.1426 4.6 32.3 6 37 2.2 2:14 94 repeat run #347350 R350 46.5 174 14.14 14.76 41.1 73.5 0.2640 19.1 72.4 22 77 3.8 2:37 21 all nozzles, delta=0 deg, alpha=0 deg, IRT air off, steam on, A&B strips.351 R351 47.6 175 14.2 14.75 42.2 73.1 0.2593 18.8 72.6 22 77 3.8 2:50 21 repeat run #350352 R352 43.8 176 14.2 14.75 38.4 73.7 0.2613 18.9 72.4 22 77 3.8 3:00 21 repeat run #350353 R353 44.6 175 14.2 14.75 39.8 73.8 0.2590 18.8 72.6 22 77 3.8 3:10 21 repeat run #350354 R354 46.4 175 14.2 14.75 40.8 73.9 0.2603 18.9 72.5 22 77 3.8 3:25 21 all nozzles, delta=0 deg, alpha=8 deg, IRT air off, steam on, B strip only.355 R355 47.3 175 14.2 14.75 41.8 74.8 0.2608 18.9 72.5 22 77 3.8 3:37 21 repeat run #354356 R356 45 175 14.2 14.76 39.7 73.7 0.2617 19.0 72.4 22 77 3.8 3:46 21 repeat run #354357 R357 46.2 177 14.2 14.75 40.6 70.3 0.1275 4.2 32.7 6 37 2.2 4:01 94 all nozzles, delta=0 deg, alpha=8 deg, IRT air off, steam on, B strip only.

NASA/TM—2002-211700 413
Date : February 16, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

358 R358 48.6 176 13.98 14.52 43.1 70.9 0.1303 4.2 32.4 6 37 2.2 6:05 94 all nozzles, IRT air off, steam on, NLF-0414f, alpha=8 deg, delta=0 deg, long B-strip only.

359 R359 45 174 14 14.52 39.6 72.9 0.1309 4.3 32.5 6 37 2.2 7:11 94 repeat run #358360 R360 47.2 175 13.99 14.53 41.7 72.2 0.1443 4.7 32.6 6 37 2.2 7:23 94 repeat run #358361 R361 45.6 175 13.99 14.54 40.1 74.4 0.2574 18.7 72.5 22 77 3.8 7:42 21 all nozzles, IRT air off, steam on, NLF-0414f, alpha=8 deg, delta=0 deg, long B-strip only.362 R362 47.2 174 13.99 14.54 41.7 70.5 0.2559 18.5 72.5 22 77 3.8 7:52 21 repeat run #361363 R363 47.7 174 13.99 14.54 42.1 70.1 0.6098 38.2 62.6 43 67 9 8:08 11 all nozzles, IRT air off, steam on, NLF-0414f, alpha=8 deg, delta=0 deg, long B-strip only.364 R364 44.1 174 13.99 14.54 38.7 75.1 0.6139 38.4 62.6 43 67 9 8:14 11 repeat run #363365 R365 46.5 175 13.99 14.53 40.9 73 0.6044 38.0 62.9 43 67 9 8:25 11 all nozzles, IRT air off, steam on, NLF-0414f, alpha=4 deg, delta=0 deg, short A & B strips.366 R366 45.7 175 13.99 14.53 40.3 70.8 0.6045 37.8 62.5 43 67 9 8:34 11 repeat run #365367 R367 46 175 13.99 14.54 40.5 69.9 0.6075 38.0 62.5 43 67 9 8:40 11 repeat run #365368 R368 46.7 175 13.99 14.53 41.3 69.1 0.2596 18.8 72.3 22 77 3.8 8:55 21 all nozzles, IRT air off, steam on, NLF-0414f, alpha=4 deg, delta=0 deg, long B-strip only.369 R369 46.5 175 14 14.54 41.4 65.5 0.2593 18.8 72.3 22 77 3.8 9:14 21 repeat run #368370 R370 44.4 175 13.99 14.54 38.9 74.8 0.2571 18.7 72.6 22 77 3.8 9:27 21 repeat run #368371 R371 45.5 175 13.99 14.53 40 71.2 0.2572 18.6 72.3 22 77 3.8 9:38 21 repeat run #368372 R372 46.8 175 13.65 14.19 41.1 71.4 0.1414 4.6 32.3 6 37 2.2 9:52 94 all nozzles, IRT air off, steam on, NLF-0414f, alpha=4 deg, delta=0 deg, long B-strip only.373 R373 45 175 13.99 14.52 39.5 70.1 0.1450 4.7 32.5 6 37 2.2 10:02 94 repeat run #372374 R374 45.6 175 13.99 14.53 40.2 71 0.1447 4.7 32.3 6 37 2.2 10:15 94 repeat run #372375 R375 46.6 149 14.12 14.52 42.7 72.1 0.1478 4.8 32.6 6 37 2.2 10:21 94 all nozzles, IRT air off, steam on, NLF-0414f, splashing test, alpha=0 deg, delta=0 deg, short B-strip.376 R376 45 100 14.34 14.52 43.3 70.7 0.1482 4.8 32.2 6 37 2.2 10:30 94 all nozzles, IRT air off, steam on, NLF-0414f, splashing test, alpha=0 deg, delta=0 deg, short B-strip.377 R377 44.8 50 14.47 14.52 44.4 70.1 0.1448 4.7 32.3 6 37 2.2 10:36 94 all nozzles, IRT air off, steam on, NLF-0414f, splashing test, alpha=0 deg, delta=0 deg, short B-strip.378 R378 44.4 50 14.47 14.51 44.2 73.2 0.1352 4.4 32.6 6 37 2.2 10:41 94 all nozzles, IRT air off, steam on, NLF-0414f, splashing test, alpha=0 deg, delta=0 deg, short B-strip.379 R379 44.8 100 14.34 14.52 43 72.1 0.1474 4.7 32.2 6 37 2.2 10:46 94 all nozzles, IRT air off, steam on, NLF-0414f, splashing test, alpha=0 deg, delta=0 deg, short B-strip.380 R380 45.6 151 14.11 14.52 41.6 73.5 0.1465 4.7 32.3 6 37 2.2 10:51 94 all nozzles, IRT air off, steam on, NLF-0414f, splashing test, alpha=0 deg, delta=0 deg, short B-strip.

NASA/TM—2002-211700 414
Date : February 17, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

381 R381 40 pressure data

382 R382 46.1 176 13.76 14.3 40.5 78.1 0.6055 37.9 62.7 43 67 9 5:08 11 NLF-414, alpha=0 deg, all nozzles, IRT air off, short A and B strips.383 R383 47.9 176 13.75 14.29 42.2 75 0.6102 38.2 62.6 43 67 9 5:27 11 repeat run #382384 R384 46 176 13.75 14.3 40.4 72.7 0.6083 38.1 62.6 43 67 9 5:39 11 repeat run #382385 R385 42.2 175 13.76 14.29 42.1 72.7 0.6104 38.3 62.7 43 67 9 5:52 11 NLF-414, alpha=8 deg, all nozzles, IRT air off, short A and B strips.386 R386 44.8 176 13.76 14.3 39.2 77.2 0.6063 38.2 63.1 43 67 9 6:19 11 repeat run #385387 R387 41.7 177 13.75 14.29 47.2 77.8 0.6027 38.1 63.2 43 67 9 6:33 11 repeat run #385388 R388 46.8 176 13.76 14.29 41.2 73.7 0.2632 19.1 72.5 22 77 3.8 6:46 21 NLF-414, alpha=8 deg, all nozzles, IRT air off, short A and B strips.389 R389 46.9 177 13.76 14.29 41.3 71.6 0.2554 18.5 72.5 22 77 3.8 6:54 21 repeat run #388390 R390 49.2 177 13.76 14.29 43.7 73.8 0.2587 18.8 72.5 22 77 3.8 7:07 21 repeat run #388391 R391 47.4 175 13.76 14.29 41.8 72.9 0.2582 18.7 72.6 22 77 3.8 7:21 21 NLF-414, alpha=0 deg, all nozzles, IRT air off, short A and B strips.392 R392 47.2 176 13.76 14.3 41.7 71.9 0.2567 18.6 72.4 22 77 3.8 7:35 21 repeat run #391393 R393 48.2 176 13.77 14.3 42.7 71 0.2565 18.6 72.4 22 77 3.8 7:45 21 repeat run #391394 R394 45.3 174 13.77 14.3 39.7 71.9 0.1358 4.4 32.5 6 37 2.2 7:57 94 NLF-414, alpha=0 deg, all nozzles, IRT air off, long B-strip and short A-strip.395 R395 45.4 175 13.76 14.3 39.9 71.9 0.1450 4.7 32.4 6 37 2.2 8:07 94 repeat run #394, short A and B strips.396 R396 48.1 176 13.76 14.3 42.6 74.2 0.1350 4.4 32.4 6 37 2.2 8:17 94 repeat run #394, short A and B strips.397 R397 46.2 177 13.76 14.3 40.7 73.9 0.1591 5.2 32.5 6 37 2.2 8:38 94 NLF-414, alpha=8 deg, all nozzles, IRT air off, long B-strip and short A-strip.398 R398 46.5 176 13.76 14.3 41.1 70.6 0.1554 5.0 32.4 6 37 2.2 8:47 94 repeat run #397, short A and B strips.399 R399 46.9 176 13.76 14.3 41.3 70.5 0.1326 4.3 32.5 6 37 2.2 8:55 94 repeat run #397, short A and B strips.400 R400 46.7 176 13.75 14.3 41.2 74 6 37 2.2 10:29 94 collector mechanism, all nozzles, IRT air off, I-strip only.401 R401 48.3 176 13.76 14.3 42.7 73.2 6 37 2.2 10:36 94 repeat run #400402 R402 47.6 176 13.77 14.3 42.1 70.3 22 77 3.8 10:45 21 collector mechanism, all nozzles, IRT air off, I-strip only.403 R403 46.8 176 13.77 14.3 41.3 70.8 22 77 3.8 10:51 21 repeat run #402404 R404 46.5 176 13.77 14.31 40.9 71 43 67 9 11:00 11

405 R405 46.5 176 13.76 14.3 41.1 70.8 43 67 9 11:07 11 repeat run#404

NASA/TM—2002-211700 415
Date : February 18, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

406 R406 46.7 177 13.78 14.32 41.2 67.4 0.2590 18.7 72.3 22 77 60 6:15 21 Collector, taking laser image, alpha=0 deg, movie (10 frames, 4 sec/frame).

407 R407 46.4 177 13.78 14.32 40.8 70.5 0.2611 19.0 72.7 22 77 3.8 6:17 21 Collector, taking laser image, alpha=0 deg, static image (exposure 4 sec).408 R408 46.4 177 13.78 14.32 40.8 67.3 0.2625 19.1 72.7 22 77 3.8 6:20 21 Collector, taking laser image, alpha=0 deg, static image (exposure 5 sec).409 R409 44.8 176 13.78 14.32 39.2 68.2 0.1556 5.1 32.6 6 37 60 6:26 94 Collector, taking laser image, alpha=0 deg, movie (10 frames, 2.2 sec/frame).410 R410 45.9 176 13.78 14.32 40.2 70.9 0.1538 5.0 32.6 6 37 2.2 6:29 94 Collector, taking laser image, alpha=0 deg, static image (exposure 3.2 sec).411 R411 43.9 178 13.78 14.32 38.3 78.6 0.6064 38.2 62.9 43 67 60 6:50 11 Collector, taking laser image, alpha=0 deg, movie (10 frames, 4 sec/frame).412 R412 47.2 176 13.78 14.33 41.5 74.7 0.6093 38.2 62.7 43 67 9 6:55 11 Collector, taking laser image, alpha=0 deg, static image (exposure 10 sec).413 R413 46.5 175 13.78 14.33 40.9 75.9 0.6044 38.2 63.2 43 67 60 7:19 11 No collector, taking laser image, movie (10 frames, 4 sec/frame).414 R414 46.7 175 13.78 14.33 41.2 75 0.6035 38.0 62.9 43 67 9 7:22 11 No collector, taking laser image, static image (exposure 10 sec).415 R415 46.4 176 13.78 14.33 40.8 72.5 0.1383 4.5 32.7 6 37 60 7:26 94 No collector, taking laser image, movie (10 frames, 2.2 sec/frame).416 R416 46.4 175 13.78 14.33 40.9 69.8 0.1335 4.3 32.4 6 37 2.2 7:28 94 No collector, taking laser image, static image (exposure 3.2 sec).417 R417 46.3 176 13.78 14.33 40.8 71.3 0.1267 4.1 32.5 6 37 2.2 7:31 94 No collector, taking laser image, static image (exposure 3.2 sec).418 R418 46.3 176 13.78 14.33 40.9 71 0.2612 19.0 72.9 22 77 60 7:35 21 No collector, taking laser image, movie (10 frames, 4 sec/frame).419 R419 45.1 176 13.78 14.33 39.6 74 0.2580 18.7 72.5 22 77 3.8 7:43 21 No collector, taking laser image, static image (exposure 5 sec).420 R420 47.3 176 13.79 14.33 41.8 76.6 0.6107 38.3 62.7 43 67 9 8:24 11 Collector, I-strip only, alpha=0 deg.421 R421 46.3 176 13.79 14.33 40.7 72.6 0.6079 38.0 62.4 43 67 9 8:33 11 repeat run #420422 R422 45.8 176 13.79 14.33 40.3 71.9 0.6047 38.2 63.2 43 67 9 8:40 11 repeat run #420423 R423 46 176 13.79 14.33 40.5 75.3 0.6057 38.2 63.0 43 67 9 8:46 11 repeat run #420424 R424 44.7 176 13.79 14.33 39.2 74 0.1263 4.1 32.6 6 37 2.2 8:54 94 Collector, I-strip only, alpha=0 deg.425 R425 44.4 176 13.79 14.33 38.9 70.6 0.1515 4.9 32.3 6 37 2.2 9:01 94 repeat run #424426 R426 45 176 13.79 14.33 39.6 73.4 0.1318 4.3 32.8 6 37 2.2 9:07 94 repeat run #424427 R427 47 176 13.79 14.33 41.4 74.4 0.1305 4.2 32.5 6 37 2.2 9:16 94 repeat run #424428 R428 43.5 176 13.79 14.33 38 74.6 0.2639 19.2 72.7 22 77 3.8 9:26 21 Collector, I-strip only, alpha=0 deg.429 R429 43.5 176 13.79 14.33 38 70.7 0.2611 19.0 72.6 22 77 3.8 9:32 21 repeat run #428430 R430 44.3 176 13.79 14.33 38.8 75.2 0.2617 19.0 72.6 22 77 3.8 9:39 21 repeat run #428431 R431 46.2 175 13.79 14.33 40.7 72.3 0.2561 18.6 72.7 22 77 3.8 9:55 21 Collector, I-strip only, alpha=8 deg.432 R432 43.2 176 13.79 14.33 37.6 76 0.2657 19.3 72.5 22 77 3.8 10:03 21 repeat run #431433 R433 43.3 175 13.79 14.33 37.8 72.5 0.2646 19.2 72.7 22 77 3.8 10:10 21 repeat run #431434 R434 44.3 176 13.79 14.32 38.9 73.2 0.1382 4.5 32.6 6 37 2.2 10:20 94 Collector, I-strip only, alpha=8 deg.435 R435 46.6 176 13.78 14.32 41.1 74.7 0.1266 4.1 32.5 6 37 2.2 10:28 94 repeat run #434436 R436 44.4 176 13.78 14.32 38.9 73.8 0.1311 4.2 32.4 6 37 2.2 10:37 94 repeat run #434437 R437 43.6 176 13.79 14.32 38.1 69.7 0.6105 38.3 62.7 43 67 9 10:46 11 Collector, I-strip only, alpha=8 deg.438 R438 44.5 176 13.79 14.32 38.9 76.8 0.6094 38.3 62.9 43 67 9 10:54 11 repeat run #437439 R439 46.4 175 13.79 14.32 40.9 73.5 0.6082 38.2 62.8 43 67 9 11:02 11 repeat run #437

NASA/TM—2002-211700 416
Date : February 19, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

440 R440 49.1 177 13.79 14.33 43.5 68.6 0.2606 18.8 72.0 22 77 3.8 5:33 21 IRT alpha=7.5 deg, true alpha=6 deg, L45FS, delta=3 deg, steam on, IRT air off, V-strips (A, B, C and D)

441 R441 45.2 176 13.76 14.33 39.6 70.2 0.2615 18.9 72.4 22 77 3.8 5:59 21 repeat run #440442 R442 47 176 13.79 14.33 41.4 77.1 0.2657 19.2 72.2 22 77 3.8 6:20 21 repeat run #440443 R443 45.3 176 13.79 14.33 39.8 72.8 0.2595 18.8 72.4 22 77 3.8 6:46 21 IRT alpha=2.5 deg, true alpha=1 deg, L45FS, delta=0 deg, steam on, IRT air off, V-strips (A and B)444 R444 46.6 176 13.81 14.35 41 73.3 0.2634 19.1 72.5 22 77 3.8 6:56 21 repeat run #443445 R445 46.6 176 13.81 14.34 40.9 73 0.2603 18.9 72.6 22 77 3.8 7:05 21 repeat run #443446 R446 46.5 176 13.8 14.33 41 71.3 0.6084 38.0 62.4 43 67 9 7:20 11 IRT alpha=2.5 deg, true alpha=1 deg, L45FS, delta=0 deg, steam on, IRT air off, V-strips (A and B)447 R447 46.7 176 13.8 14.34 41.1 71.6 0.6062 38.2 63.1 43 67 9 7:34 11 repeat run #446448 R448 45.3 176 13.8 14.34 39.8 72.2 0.6060 38.0 62.8 43 67 9 7:44 11 repeat run #446449 R449 45.9 176 13.8 14.34 40.5 72.8 0.1594 5.1 32.3 6 37 2.2 7:54 94 IRT alpha=2.5 deg, true alpha=1 deg, L45FS, delta=0 deg, steam on, IRT air off, V-strips (A and B)450 R450 45 176 13.8 14.34 39.5 73.1 0.1287 4.2 32.5 6 37 2.2 8:06 94 repeat run #449451 R451 46.2 176 13.8 14.34 40.6 71 0.1517 4.9 32.3 6 37 2.2 8:19 94 repeat run #449452 R452 45 175 13.8 14.34 40.9 72.8 0.2593 18.8 72.5 22 77 3.8 8:41 21 IRT alpha=7.5 deg, true alpha=6 deg, L45FS, delta=0 deg, steam on, IRT air off, V-strips (A and B)453 R453 45.1 174 13.8 14.34 39.7 71.7 0.2568 18.7 72.7 22 77 3.8 8:57 21 repeat run #452454 R454 47.2 175 13.79 14.34 41.5 72.8 0.2619 19.0 72.5 22 77 3.8 9:10 21 repeat run #452455 R455 45.2 176 13.8 14.34 39.9 73 0.2628 19.0 72.4 22 77 3.8 9:40 21 IRT alpha=3.5 deg, true alpha=2 deg, L45FS, delta=3 deg, steam on, IRT air off, V-strips (A and D)456 R456 45 176 13.8 14.34 39.4 74.2 0.2591 18.8 72.7 22 77 3.8 9:55 21 repeat run #455457 R457 44.9 175 13.8 14.34 39.4 72.8 0.2648 19.2 72.6 22 77 3.8 10:04 21 repeat run #455

NASA/TM—2002-211700 417
Date : February 20, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

458 R458 51.5 176 13.85 14.8 46 70.2 0.1462 4.8 32.5 6 37 2.2 10:01 94 Collector mechanism, alpha=0 deg, strips G, I and C.

459 R459 49.5 175 13.84 14.38 44 71.5 0.1440 4.6 32.2 6 37 2.2 10:10 94 repeat run #458460 R460 47.8 175 13.84 14.38 42.2 71.3 0.1478 4.8 32.3 6 37 2.2 10:27 94 repeat run #458461 R461 48.4 175 13.84 14.37 43 71.7 0.6162 38.4 62.4 43 67 9 10:46 11 Collector mechanism, alpha=0 deg, strips G, I and C. (A redo run, previous set of strips were wetted)462 R462 47.8 176 13.84 14.38 42.2 71 0.6028 37.9 62.8 43 67 9 10:52 11 repeat run #461463 R463 49.8 175 13.86 14.38 44.4 72.1 0.6101 38.2 62.7 43 67 9 11:04 11 repeat run #461464 R464 51 176 13.85 14.38 45.7 70.9 0.2664 19.3 72.5 22 77 3.8 11:14 21 Collector mechanism, alpha=0 deg, strips G, I and C.465 R465 48.9 176 13.85 14.38 43.4 71.2 0.2573 18.6 72.3 22 77 3.8 11:21 21 repeat run #464466 R466 48.6 176 13.85 14.38 43.2 70.4 0.2675 19.3 72.1 22 77 3.8 11:27 21 repeat run #464467 R467 49.3 150 13.97 14.38 45.2 71.3 0.1353 4.3 32.1 6 37 2.2 11:40 94 Collector mechanism, splashing test, alpha=0 deg, strips G, I and C.468 R468 51.1 150 13.99 14.38 47.2 75 0.1253 4.1 32.7 6 37 2.2 11:49 94 repeat run #467469 R469 49.1 101 14.2 14.38 47.2 70.7 0.1379 4.4 32.1 6 37 2.2 12:00 94 Collector mechanism, splashing test, alpha=0 deg, strips G, I and C.470 R470 48.8 100 14.2 14.37 47.1 73.3 0.1265 4.1 32.3 6 37 2.2 12:05 94 repeat run #469471 R471 48.8 50 14.33 14.38 48.4 73.8 0.1495 4.8 32.3 6 37 2.2 12:11 94 Collector mechanism, splashing test, alpha=0 deg, strips G, I and C.472 R472 48.9 50 14.33 14.38 48.4 74.1 0.1324 4.3 32.2 6 37 2.2 12:21 94 repeat run #471473 R473 50.9 175 13.84 14.38 45.5 72.7 0.2616 18.9 72.4 22 77 3.8 12:41 21 Collector mechanism, alpha=8 deg, strips G, I and C.474 R474 48.7 175 13.84 14.38 43.1 73.7 0.2647 19.1 72.0 22 77 3.8 1:00 21 repeat run #473475 R475 49.6 174 13.84 14.37 44 76 0.2556 18.6 72.6 22 77 3.8 1:07 21 repeat run #473476 R476 49.6 175 13.84 14.38 44.2 69.7 0.2574 18.6 72.4 22 77 3.8 1:20 21 Collector mechanism, alpha=8 deg, I-strip only.477 R477 48.5 175 13.84 14.37 42.9 73.6 0.2546 18.5 72.5 22 77 3.8 1:26 21 repeat run #476478 R478 48 174 13.84 14.37 42.6 70.6 0.1565 5.0 32.2 6 37 2.2 1:35 94 Collector mechanism, alpha=8 deg, I-strip only.479 R479 48.4 175 13.84 14.37 42.7 71.3 0.1599 5.2 32.3 6 37 2.2 1:42 94 repeat run #478480 R480 51 175 13.84 14.37 45.4 75.6 0.6147 38.3 62.2 43 67 9 1:56 11 Collector mechanism, alpha=8 deg, I-strip only.481 R481 49 174 13.84 14.36 43.5 73.5 0.6125 38.2 62.4 43 67 9 2:03 11 repeat run #480482 R482 48.9 174 13.84 14.37 43.4 72.5 0.6118 38.1 62.4 43 67 9 2:09 11 repeat run #480483 R483 47.3 176 13.83 14.36 41.8 71.7 0.6086 38.2 62.8 43 67 9 3:40 11 Uniformity grid with collector strips size484 R484 48.8 176 13.84 14.37 43.2 75.1 0.2652 19.2 72.5 22 77 3.8 4:17 21 Uniformity grid with collector strips size485 R485 49.6 176 13.84 14.37 43.8 74.2 0.1291 4.2 32.3 6 37 2.2 4:56 94 Uniformity grid with collector strips size

NASA/TM—2002-211700 418
Date : February 22, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

486 R486 BJE, pressure data, alpha=7, 6, 5, 4, 3, 2, 1, 0 degs.

NASA/TM—2002-211700 419
Date : February 23, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

487 R487 49 176 13.87 14.41 43.5 73.2 0.6053 38.0 62.8 43 67 9 4:31 11 All nozzles, steam on, IRT air off, BJE, A and B strips, delta=0 deg, alpha=1 deg.

488 R488 47.8 176 13.88 14.42 42.2 71.9 0.6083 38.2 62.8 43 67 9 4:46 11 repeat run #487489 R489 46.1 176 13.87 14.42 40.5 72.2 0.6123 38.4 62.7 43 67 9 5:00 11 repeat run #487490 R490 46.5 176 13.88 14.42 41 72 0.2559 18.6 72.8 22 77 3.8 5:16 21 All nozzles, steam on, IRT air off, BJE, A and B strips, delta=0 deg, alpha=1 deg.491 R491 50.1 176 13.88 14.42 44.6 73.2 0.2635 19.2 72.9 22 77 3.8 5:35 21 repeat run #490492 R492 45.7 177 13.88 14.42 40 74.6 0.2591 18.8 72.6 22 77 3.8 5:51 21 repeat run #490493 R493 45.7 175 13.88 14.42 40.1 72.9 6 37 2.2 6:06 94 All nozzles, steam on, IRT air off, BJE, A and B strips, delta=0 deg, alpha=1 deg.494 R494 46.9 176 13.88 14.42 41.2 73.4 0.1538 5.0 32.8 6 37 2.2 6:19 94 repeat run #493495 R495 48.5 175 13.88 14.42 43 71.6 0.1562 5.1 32.6 6 37 2.2 6:30 94 repeat run #493496 R496 47 175 13.88 14.43 41.5 71 0.1583 5.1 32.4 6 37 2.2 6:45 94 All nozzles, steam on, IRT air off, BJE, A and B strips, delta=0 deg, alpha=6 deg.497 R497 47.5 174 13.88 14.43 42 72.5 0.1284 4.2 32.4 6 37 2.2 7:00 94 repeat run #496498 R498 46.4 174 13.88 14.43 40.9 71.3 0.1347 4.4 32.7 6 37 2.2 7:12 94 repeat run #496499 R499 45.6 175 13.88 14.42 40.1 73.3 0.6013 38.0 63.2 43 67 9 7:23 11 All nozzles, steam on, IRT air off, BJE, A and B strips, delta=0 deg, alpha=6 deg.500 R500 46 174 13.89 14.43 40.5 74.5 0.6096 38.3 62.8 43 67 9 7:40 11 repeat run #499501 R501 47.5 175 13.88 14.42 42.1 74.9 0.6068 38.1 62.9 43 67 9 7:54 11 repeat run #499502 R502 46.5 174 13.88 14.42 41.1 72.9 0.2606 19.0 72.8 22 77 3.8 8:07 21 All nozzles, steam on, IRT air off, BJE, A and B strips, delta=0 deg, alpha=6 deg.503 R503 48.4 175 13.88 14.42 42.9 73.6 0.2623 19.0 72.4 22 77 3.8 8:24 21 repeat run #502504 R504 47.4 175 13.88 14.42 41.9 71.6 0.2616 19.0 72.7 22 77 3.8 8:32 21 repeat run #502505 R505 45.5 176 13.88 14.42 40 73.2 0.6101 38.4 62.9 43 67 9 10:18 11 All nozzles, steam on, IRT air off, BJE, A and B strips, delta=10 deg, alpha=1 deg.506 R506 47.8 174 13.89 14.42 42.6 75.6 0.6053 38.0 62.8 43 67 9 10:30 11 repeat run #505507 R507 46.5 175 13.89 14.42 41.2 75.2 0.6073 38.4 63.2 43 67 9 10:54 11 repeat run #505

NASA/TM—2002-211700 420
Date : February 24, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

508 R508 47.7 176 13.86 14.4 42.1 75.1 0.6076 38.1 62.7 43 67 30 5:27 11 10 frames, 2 sec/fr, laser image, clean tunnel, steam on, IRT air off, all nozzles.

509 R509 49 176 13.86 14.41 43.5 75.9 0.6027 37.8 62.7 43 67 9 5:30 11 1 frame, 10 sec/fr, laser image, clean tunnel, steam on, IRT air off, all nozzles.510 R510 46.3 176 13.87 14.41 40.8 72.7 0.2610 19.0 72.7 22 77 30 5:34 21 10 frames, 2 sec/fr, laser image, clean tunnel, steam on, IRT air off, all nozzles.511 R511 47 176 13.87 14.4 41.5 75.7 0.2583 18.7 72.5 22 77 3.8 5:36 21 1 frame, 5 sec/fr, laser image, clean tunnel, steam on, IRT air off, all nozzles.512 R512 46.3 176 13.85 14.4 40.7 73.6 0.1322 4.3 32.4 6 37 30 5:41 94 10 frames, 2 sec/fr, laser image, clean tunnel, steam on, IRT air off, all nozzles.513 R513 47.1 176 13.86 14.34 41.5 75.8 0.1407 4.6 32.4 6 37 2.2 5:43 94 1 frame, 3.2 sec/fr, laser image, clean tunnel, steam on, IRT air off, all nozzles.514 R514 47.8 176 13.86 14.39 42.3 71.6 0.1572 5.1 32.5 6 37 2.2 6:43 94 Collector mechanism, BJE, all nozzles, IRT air off, steam on, I-mod strip at B-strip location.515 R515 44 176 13.84 14.39 38.7 74.7 0.1429 4.6 32.2 6 37 2.2 6:49 94 repeat run #514516 R516 45 176 13.84 14.39 39.2 74.1 0.1546 5.0 32.5 6 37 2.2 6:54 94 repeat run #514517 R517 46.2 175 13.85 14.39 40.7 77.2 0.6097 38.2 62.7 43 67 9 7:03 11 Collector mechanism, BJE, all nozzles, IRT air off, steam on, I-mod strip at B-strip location.518 R518 45.6 174 13.85 14.39 40.3 76.4 0.6089 38.2 62.7 43 67 9 7:10 11 repeat run #517519 R519 44.2 177 13.86 14.39 38.6 75.3 0.6036 37.9 62.8 43 67 9 7:24 11 repeat run #517520 R520 48.2 177 13.84 14.38 42.9 74.8 0.2586 18.8 72.8 22 77 3.8 7:36 21 Collector mechanism, BJE, all nozzles, IRT air off, steam on, I-mod strip at B-strip location.521 R521 45.8 177 13.84 14.38 40.2 74.6 0.2581 18.8 72.7 22 77 3.8 7:42 21 repeat run #520522 R522 45.8 176 13.84 14.38 40.1 75.3 0.2639 19.2 72.6 22 77 3.8 7:49 21 repeat run #520523 R523 46 176 13.83 14.38 40.4 74.3 0.2655 19.3 72.7 22 77 3.8 8:06 21 Collector mechanism, BJE, all nozzles, IRT air off, steam on, I-mod strip at A-strip location.524 R524 50.6 177 13.83 14.38 45.1 73.6 0.2605 18.8 72.3 22 77 3.8 8:20 21 repeat run #523525 R525 47.6 177 13.83 14.37 41.9 75.9 0.2650 19.2 72.4 22 77 3.8 8:32 21 repeat run #523526 R526 46.2 175 13.83 14.38 40.8 75.7 0.6052 38.2 63.2 43 67 9 8:44 11 Collector mechanism, BJE, all nozzles, IRT air off, steam on, I-mod strip at A-strip location and E-strip,527 R527 46.2 175 13.84 14.38 40.7 74.8 0.6040 37.9 62.7 43 67 9 8:50 11 repeat run #526528 R528 48.4 175 13.84 14.38 42.9 75.7 0.6103 38.3 62.8 43 67 9 9:00 11 repeat run #526529 R529 46.9 174 13.84 14.37 41.4 73 0.1366 4.4 32.4 6 37 2.2 9:07 94 Collector mechanism, BJE, all nozzles, IRT air off, steam on, I-mod strip at A-strip location and E-strip,530 R530 46.1 175 13.84 14.38 40.6 72.3 0.1380 4.5 32.5 6 37 2.2 9:14 94 repeat run #529531 R531 45.9 175 13.83 14.38 40.4 71.7 0.1402 4.5 32.3 6 37 2.2 9:20 94 repeat run #529532 R532 48.3 174 13.84 14.37 42.8 74.1 0.1365 4.4 32.5 6 37 2.2 9:34 94 Collector mechanism at center of turntable (normal position), I-strip, all nozzles, IRT air off, steam on.533 R533 46.3 174 13.84 14.37 40.8 75.2 0.6059 38.2 63.1 43 67 9 9:46 11 Collector mechanism at center of turntable (normal position), I-strip, all nozzles, IRT air off, steam on.534 R534 45.9 174 13.83 14.36 40.6 74.5 0.2535 18.4 72.7 22 77 3.8 9:54 21 Collector mechanism at center of turntable (normal position), I-strip, all nozzles, IRT air off, steam on.

Note: No run performed on February 25, 1999.

NASA/TM—2002-211700 421
Date : February 26, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

535 R535 pressure data (rdg #6725 to #6730).

took video of laser image for MVD 21 without and with mass flow of 23 lbs/sec.took another few video of laser image of other MVD.

536 R536 49.1 170 13.84 14.36 43.8 74.5 6 37 2.2 8:16 94 S-duct inlet, all nozzles, steam on, strips A, B, C and D, mass flow = 23 lbs/s, scavenge flow = 2 lbs/s.537 R537 50.5 169 13.86 14.37 45.4 71.6 6 37 2.2 8:53 94 repeat run #536538 R538 50.2 170 13.86 14.37 44.9 73.7 6 37 2.2 9:20 94 repeat run #536539 R539 48.8 170 13.86 14.36 43.4 72.6 22 77 3.8 9:51 21 S-duct inlet, all nozzles, steam on, strips A, B, C and D, mass flow = 23 lbs/s, scavenge flow = 2 lbs/s.540 R540 47 169 13.86 14.36 41.8 67.1 22 77 3.8 10:21 21 repeat run #539541 R541 50 169 13.86 14.36 44.8 72.3 22 77 3.8 10:46 21 repeat run #539

NASA/TM—2002-211700 422
Date : February 27, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

542 R542 49.4 131 13.97 14.26 46.5 75 0.2609 18.8 72.0 22 77 3.8 10:05 21 S-duct inlet, all nozzles, steam on, strips A, B, C and D, mass flow = 23 lbs/s, scavenge flow = 1.5 lbs/s.

543 R543 49.4 130 13.96 14.25 46.3 74.3 0.2642 19.1 72.3 22 77 3.8 10:29 21 repeat run #542544 R544 48 130 13.96 14.25 45 74.4 0.2635 19.0 72.3 22 77 3.8 10:50 21 repeat run #542545 R545 50.4 131 13.94 14.24 47.4 68.7 0.1438 4.7 32.3 6 37 2.2 11:27 94 S-duct inlet, all nozzles, steam on, strips A, B, C and D, mass flow = 23 lbs/s, scavenge flow = 1.5 lbs/s546 R546 50.6 131 13.94 14.23 47.6 71.8 0.1488 4.8 32.0 6 37 2.2 11:55 94 repeat run #545547 R547 49.1 131 13.92 14.22 46.1 74.5 0.1455 4.7 32.2 6 37 2.2 12:25 94 repeat run #545548 R548 50.5 169 13.71 14.21 45.4 71.5 0.6150 38.4 62.4 43 67 9 12:50 11 S-duct inlet, all nozzles, steam on, strips A, B, C and D, mass flow = 23 lbs/s, scavenge flow = 2 lbs/s549 R549 51.3 170 13.7 14.21 46 72.6 0.6066 38.4 63.2 43 67 9 1:13 11 repeat run #548550 R550 53.2 171 13.7 14.2 47.7 74.2 0.6129 38.1 62.1 43 67 9 1:47 11 repeat run #548551 R551 55.7 169 13.69 14.19 50.4 73.5 0.1439 4.7 32.4 6 37 2.2 2:16 94 S-duct inlet, all nozzles, steam on, strips A, B, C and D, mass flow = 23 lbs/s, scavenge flow = 2 lbs/s552 R552 55.4 172 13.69 14.19 50.1 70.3 0.1407 4.5 32.2 6 37 2.2 2:45 94 repeat run #561

NASA/TM—2002-211700 423
Date : March 1, 1999 (cont.)

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

553 R553 47.4 200 40.2 63.6 120 3:33 94 Splashing test, laser sheet method. Laser sheet is normal to the chord length of MS-317. Alpha=0 deg.

video tape = 10.

554 R554 47 200 40 62 5.0 55.0 120 3:36 175 Splashing test, laser sheet method. Laser sheet is normal to the chord length of MS-317. Alpha=0 deg.

video tape = 11:40.

555 R555 47.6 200 to 50 40 63.5 6 37 150 3:40 94 Splashing test, laser sheet method. Laser sheet is normal to the chord length of MS-317. Alpha=0 deg.

video tape = 13:22. Speed is reduced after about 40 sec of spray time.

556 R556 45 50 to 200 44.5 73 22 77 150 3:45 21 Splashing test, laser sheet method. Laser sheet is normal to the chord length of MS-317. Alpha=0 deg.

video tape = 16:28. Speed is increased after about 40 sec of spray time.

557 R557 45.5 200 to 40 38.4 75.7 43 67 150 3:49 11 Splashing test, laser sheet method. Laser sheet is normal to the chord length of MS-317. Alpha=0 deg.

video tape = 18:50. Speed is reduced after about 40 sec of spray time.

558 R558 47 175 41 78 6 37 150 3:52 94 Splashing test, laser sheet method. Laser sheet is normal to the chord length of MS-317.

video tape = 21:44. AOA changed from 0 deg to 8 deg while spraying.

559 R559 48 175 43 75 6 37 150 3:56 94 Splashing test, laser sheet method. Laser sheet is normal to the chord length of MS-317. Alpha=8 deg.

video tape = 24:40.

560 R560 47.7 175 42.2 71.6 2.0 24.0 150 4:00 270 Splashing test, laser sheet method. Laser sheet is normal to the chord length of MS-317. Alpha=8 deg.

video tape = 27:33.

561 R561 45 175 39.6 70.5 2.0 24.0 120 4:06 270 Splashing test, laser sheet method. Laser sheet is normal to the chord length of MS-317. Alpha=0 deg.

video tape = 30:39.

562 R562 45.5 200 to 10 40.2 77.8 6 37 160 4:!1 94 Splashing test, laser sheet method. Laser sheet is normal to the chord length of MS-317. Alpha=0 deg.

video tape = 33:08.

563 R563 46.8 0 to 200 46.8 78.9 6 37 200 4:16 94 Splashing test, laser sheet method. Laser sheet is normal to the chord length of MS-317. Alpha=0 deg.

video tape = 36:47.

564 R564 47.4 130 13.86 14.15 44.6 72.4 0.2543 18.4 72.2 22 77 3.8 5:34 21 Collector, S-duct inlet, strips A, B, C, G, H and I.565 R565 45.8 131 13.86 14.16 42.8 72.4 0.2609 18.8 72.1 22 77 3.8 5:44 21 repeat run #564566 R566 45.4 131 13.86 14.16 42.4 72.9 0.2620 18.9 72.3 22 77 3.8 5:52 21 repeat run #564567 R567 45.8 131 13.86 14.16 42.7 75 0.2675 19.3 72.3 22 77 3.8 6:00 21 repeat run #564

NASA/TM—2002-211700 424
Date : March 1, 1999

PBAR :

DYE CONCENTRATION : 0.0003 grams/cc

PSYCHROMETER READINGS :

:

SPRAY CONDITIONS / MASS FLOW

TUNNEL CONDITION NOZZLE PRESSURE TANK TIME REMARKS

 PRESSURE

RUN Run I.D. TEMP. TAS P∞ PRESS TEMP. Humidity PAIR PAIR PWATER PAIR PWATER SPRAY SPRAY MVD

NO. Total (MPH) (PSIA) TOTAL Stat % PWATER (PSIG) (PSIG) (PSIG) (PSIG) (SEC) TIME

(oF) (PSIA) (oF) (PM)

568 R568 47.4 131 13.86 14.16 44.4 75.4 0.1333 4.3 32.2 6 37 2.2 6:12 94 Collector, S-duct inlet, strips A, B, C, G, H and I.

569 R569 47.6 131 13.86 14.16 44.6 75.5 0.1448 4.7 32.6 6 37 2.2 6:19 94 repeat run #568570 R570 47.8 131 13.86 14.16 44.7 74.9 0.1410 4.5 32.0 6 37 2.2 6:26 94 repeat run #568571 R571 46.6 171 13.67 14.16 41.4 75.7 0.6184 38.5 62.3 43 67 9 6:46 11 Collector, S-duct inlet, strips A, B, C, G, H and I.572 R572 48.8 171 13.66 14.17 43.7 76 0.6114 38.0 62.2 43 67 9 6:55 11 repeat run #571573 R573 46.2 171 13.67 14.17 40.9 74.1 0.6132 38.1 62.2 43 67 9 7:06 11 repeat run #571574 R574 46.5 171 13.66 14.17 41.2 72.8 0.2643 19.1 72.1 22 77 3.8 7:20 21 Collector, S-duct inlet, strips A, B, C, G, H and I.575 R575 49 172 13.67 14.17 43.8 72.8 0.2655 19.1 71.9 22 77 3.8 7:31 21 repeat run #574576 R576 48 171 13.66 14.17 42.8 71.8 0.2648 19.1 72.3 22 77 3.8 7:40 21 repeat run #574577 R577 47.2 171 13.67 14.18 42 72.1 0.1343 4.3 32.3 6 37 2.2 7:50 94 Collector, S-duct inlet, strips A, B, C, G, H and I.578 R578 47.5 170 13.67 14.17 42.3 75.3 0.1376 4.5 32.6 6 37 2.2 7:56 94 repeat run #577579 R579 47.8 171 13.67 14.18 42.6 73.7 0.1412 4.6 32.6 6 37 2.2 8:04 94 repeat run #577580 R580 48.8 176 13.64 14.17 43.2 72.6 0.1547 5.0 32.1 6 37 2.2 8:27 94 Collector, BJE, I-mod strip, B-location.581 R581 46.7 176 13.64 14.18 41.2 73.4 0.1450 4.7 32.6 6 37 2.2 8:40 94 repeat run #580582 R582 46.9 176 13.65 14.18 41.4 74.3 0.1445 4.7 32.6 6 37 2.2 8:46 94 repeat run #580583 R583 48.3 176 13.65 14.18 42.7 76.3 0.6113 38.2 62.5 43 67 9 8:52 11 Collector, BJE, I-mod strip, B-location.584 R584 48.4 176 13.64 14.18 43 74.5 0.6171 38.4 62.2 43 67 9 8:59 11 repeat run #583585 R585 47.2 176 13.65 14.18 41.7 74.5 0.6093 38.2 62.6 43 67 9 9:04 11 repeat run #583586 R586 46.8 176 13.65 14.18 41.3 74.2 0.2662 19.2 72.2 22 77 3.8 9:11 21 Collector, BJE, I-mod strip, B-location.587 R587 46.7 176 13.65 14.18 41.1 73.2 0.2607 18.9 72.4 22 77 3.8 9:16 21 repeat run #586588 R588 49.3 177 13.65 14.18 43.9 73.1 0.2616 18.9 72.3 22 77 3.8 9:26 21 repeat run #586589 R589 46.6 175 13.65 14.18 41.1 74.7 0.2585 18.7 72.5 22 77 3.8 9:40 21 Collector, NLF airfoils, alpha=8 deg, I-strip only.590 R590 46.5 175 13.66 14.18 41.1 74.5 0.2640 19.1 72.4 22 77 3.8 9:45 21 repeat run #589591 R591 48.7 175 13.66 14.18 43 75.6 0.2575 18.6 72.2 22 77 3.8 9:53 21 repeat run #589592 R592 48.5 175 13.65 14.18 43 74.3 0.1349 4.4 32.6 6 37 2.2 10:00 94 Splashing test, NLF-airfoil location, alpha=8 deg, I-strip only.593 R593 47.2 174 13.66 14.18 41.8 75.4 0.1315 4.3 32.4 6 37 2.2 10:07 94 repeat run #572594 R594 46.7 50 14.14 14.18 46.4 74.5 0.1562 5.1 32.6 6 37 2.2 10:14 94 Splashing test, NLF-airfoil location, alpha=8 deg, I-strip only.595 R595 45.9 50 14.14 14.18 45.5 76.3 0.1348 4.4 32.5 6 37 2.2 10:17 94 repeat run #594

NASA/TM—2002-211700 425

References 

1. Von Glahn, U., Gelder, T.F., and Smyers, W.H. Jr, “A Dye Tracer Technique for 

Experimentally Obtaining Impingement Characteristics of Arbitrary Bodies and a 

Method for Determining Droplet Size Distribution,” NACA TN–3338, March 1955. 

2. Gelder, T.F., Smyers, W.H. Jr, and Von Glahn, U., “Experimental Droplet 

Impingement on Several Two-Dimensional Airfoils with Thickness Ratios of 6 to 

16 percent,” NACA TN–3839, December 1956. 

3. Lewis, J.O. and Ruggeri, R.S., “Experimental Droplet Impingement on Four 

Bodies of Revolution,” NACA TN–3587, 1957. 

4. Lewis, James O. and Ruggeri, Robert S., “Experimental Droplet Impingement on 

four bodies of revolution,” NACA TN–4092, December 1955. 

5. Gelder, T.F., “Droplet Impingement and Ingestion by Supersonic Nose Inlet in 

Subsonic Tunnel Conditions,” NACA TN–4268, May 1958. 

6. Papadakis, M., Elangovan, R., Freund, G.A., Jr., Breer, M., Zumwalt, G.W. and 

Whitmer, L., “An Experimental Method for Measuring Water Droplet Impingement 

Efficiency on Two- and Three-Dimensional Bodies,” NASA CR–4257, 

DOT/FAA/CT–87/22, November 1989. 

7. Papadakis, M., Breer, M.D., Craig, N., and Liu, X., “Experimental Water Droplet 

Impingement Data on Airfoils, Simulated Ice Shapes, an Engine Inlet and a Finite 

Wing,” NASA CR 4636, DOT/FAA/CT–TN93/18, December 1994. 

8. Phillips, E.H. “ATR42/72 Review Focuses on Icing,” Aviation Week and Space 

Technology, November 14, 1994. 

9. Phillips, E.H. “FAA Lifts Icing Ban on ATR Flights,” Aviation Week and Space 

Technology, June 5, 1995. 

10. Miller, D.R., Addy, H.E., and Ide, R.F, “A Study of Large Droplet Ice Accretions in 

the NASA-Lewis IRT at Near-Freezing Conditions,” AIAA Paper 96–0934, 34th 

Aerospace Sciences Meeting and Exhibit, Reno, NV, January 15–18, 1996. 

11. Bragg, M.B., “Aircraft Aerodynamic Effects due to Large Droplet Ice Accretions,” 

AIAA Paper 96–0932, 34th Aerospace Sciences Meeting and Exhibit, Reno, NV, 

January 15–18, 1996. 

12. “FAA Inflight Aircraft Icing Plan,” Federal Aviation Administration, April 1997. 

13. Kim, John, “Particle Trajectory Computation on a 3-Dimensional Engine Inlet,” 

NASA CR–175023, DOT–FAA–CT–86–1, January 1986. 

14. Carlson, D.J. and Hoglund, R.F., “Particle Drag and Heat Transfer in Rocket 

Nozzles,” AIAA Journal, Vol. 2, No. 11, pp. 1980–1984, November 1964. 

15. Langmuir, I. And Blodgett, K.B., “A mathematical Investigation of Water Droplet 

Trajectories,” Army Air Forces Technical Report No. 5418, 1946. 

16. Soeder, R.H. and Andracchio, C.R., “NASA Lewis Icing Research Tunnel User 

Manual,” NASA TM–102319, June 1990. 

17. McGhee, R.J. and Beasley, W.D., “Low-Speed Aerodynamic Characteristics of a 

17-Percent-Thick Medium-Speed Airfoil Designed for General Application,” NASA 

TP–1786, 1980. 

18. Addy, H.E., Jr., Potapczuk, M.G., and Sheldon, D.W., “Modern Airfoil Ice 

Accretions,” NASA TM–107423, January 1997. 

NASA/TM—2002-211700 427
19. Torenbeek, E., “Synthesis of Subsonic Airplane Design,” Delft University Press, 

1982. 

20. Abbott, I.H. and Von Doenhoff, A.E., “Theory of Wing Sections,” Dover 

Publications, Inc., 1959. 

21. McGhee, R.J., Viken, J.K., Pfenninger, W., Beasley, W.D., and Harvey, W.D., 

“Experimental Results for a Flapped Natural-Laminar-Flow Airfoil with High 

Lift/Drag Ratio,” NASA TM–85788, May 1984. 

22. Valarezo, W.O., Dominik, C.J., McGhee, R.J., Goodman, W.L., and Paschal, 

K.B., “Multi-Element Airfoil Optimization for Maximum Lift at High Reynolds 

Numbers,” AIAA paper 91–3332, September 1991. 

23. Valarezo, W.O., Dominik, C.J., and McGhee, R.J., “Reynolds and Mach Number 

Effects on Multielement Airfoils,” Fifth Symposium on Numerical and Physical 

Aspects of Aerodynamic Flows, Long Beach, January, 1992. 

24. Batra, A.B., Bennett, W.A., Vittal, B.R., and Krishnan, M.R., "Design and 

Development of a Compact Bifurcated Turboprop Inlet," AIAA Paper 91–2017, 

June 1991. 

25. Canacci, V., Bencic, T., Krupar, M., and Potapczuk, M., “A Sheet Laser Flow 

Visualization System in NASA’s Icing Research Tunnel,” AIAA Paper 98–0342, 

January 1998. 

26. Oldenburg, J.R. and Ide, R.F., “Comparison of Drop Size Distributions From Two 

Droplet Sizing Systems,” NASA TM–102520, March 1990. 

27. “CSIRO-KING Liquid Water Content Probe PMS Model KLWC-5 – Operating and 

Servicing Manual,” Particle Measuring Systems, Inc., Boulder, Colorado. 

28. Frei, R.W. and MacNeil, J.D., “Diffuse reflectance Spectroscopy in Environmental 

Problem Solving,” CRC Press, Cleveland, Ohio, 1973. 

29. Kubelka, P., “New Contributions to the Optics of Intensely Light-Scattering 

MaterialsPart I,” Journal of the Optical Society of America, Volume 38, 1955. 

30. Bragg, M.B., Sweet, D., Waples,T., and Shick, R. “An Experimental Method for 

Water Droplet Impingement Measurement,” Proceedings of the American 

Helicopter Society/Society of Automotive Engineers, International Icing 

Symposium, Montreal Canada, September 18–21, 1995. 

31. Wright, W.B., “Users Manual for the Improved NASA Lewis Ice Accretion Code 

LEWICE 1.6,” NASA CR–198355, June 1995. 

32. Johnson, F., Samant, S., Bieterman, M., Melvin, R., Young, D., Bussoletti, J., and 

Hilmes, C., “TranAir: A Full-Potential, Solution-Adaptive, Rectangular Grid Code 

for Predicting Subsonic, Transonic, and Supersonic flows about Arbitrary 

Configurations,” NASA CR–4348, December 1982. 

33. Ashby, D., Dudley, M., and Iguchi, S., “Development and Validation of an 

Advanced Low-Order Panel Method,” NASA TM–101024, October 1988. 

34. Papadakis, M., Hung, K.E., Bidwell, C., and Breer, M., “Experimental 

Investigation of Water Impingement on Single and Multi-Element Airfoils,” AIAA 

Paper 2000–0100, 38th Aerospace Sciences Meeting and Exhibit, Reno, NV, 

January 10–13, 2000. 

35. Potapczuk, M. and Bidwell, C., “Swept Wing Ice Accretion Modeling,” NASA TM–

103114, January 1990. 

NASA/TM—2002-211700 428
36. Potapczuk, M. and Bidwell, C., “Numerical Simulation of Ice Growth on a MS-317 

Swept Wing Geometry,” NASA TM–103705, January 1991. 

37. Reehorst, A., “Prediction of Ice Accretion on a Swept NACA 0012 Airfoil and 

Comparisons to flight test Results,” NASA TM–105368, January 1992. 

38. Mohler, S. and Bidwell, C., “Comparison of Two-Dimensional and ThreeDimensional Droplet Trajectory Calculations in the Vicinity of Finite Wings,” NASA 

TM–105617, January 1992. 

39. Bidwell, C. and Mohler, S., “Collection Efficiency and Ice Accretion Calculations 

for a Sphere, a Swept MS(1)-317 Wing, a Swept NACA–0012 Wing Tip, an 

Axisymmetric Inlet, and a Boeing 737-300 Inlet,” NASA TM–106831, January 

1995. 

40. Bidwell, C., Pinella, D., and Garrison, P., “Ice Accretion Calculations for 

Commercial Transport Using the LEWICE-3D, ICEGRID3D, and CMARC 

Programs,” NASA/TM1999-208895, January 1999. 

41. Al-Khalil, K., Hitzigrath, R., Phillippi, O. and Bidwell, C., “Icing Analysis and Test 

of a Business Jet Engine Inlet Duct,” AIAA Paper 2000–1040, 38th Aerospace 

Sciences Meeting and Exhibit, Reno, NV, January 10–13, 2000. 

42. Bidwell, C. and Potapczuk, M., “Users Manual for the NASA Lewis ThreeDimensional Ice Accretion Code (LEWICE-3D),” NASA TM–105974, December 

1993. 

43. Norment, H., “Calculation of Water Drop Trajectories To and About ThreeDimensional Lifting and Non-lifting bodies in Potential Airflow,” NASA CR–3935, 

October 1985. 

44. Krogh, F., “Variable Order Integrators for Numerical Solutions of Ordinary 

Differential Equations,” Jet Propulsion Lab Technology Utilization Document No. 

CP–32308, November 1970. 

45. Ide, R.F, private communication, April 16, 1996. 

46. Ide, R.F., “Liquid Water Content and Droplet Size Calibration of the NASA Lewis 

Icing Research Tunnel,” AIAA Paper 90–0669, 28th Aerospace Sciences Meeting 

and Exhibit, Reno, NV, January 8–11, 1990. 

47. Rogers, S.E. and Kwak, D., “An Upwind Differencing Scheme for the Steady 

State Incompressible Navier-Stokes Equations,” NASA TM–101051, November 

1988. 

48. Rogers, S.E. and Kwak, D., “An Upwind Differencing Scheme for the Time 

Accurate Incompressible Navier-Stokes Equations,” AIAA Journal, Vol. 28, No. 2, 

February 1990, pp. 253–262. 

49. Power, G.D., Cooper, G.K., and Sirbaugh, J.R., "NPARC 2.2Features and 

Capabilities," AIAA Paper 95–2609, 1995. 

50. Papadakis, M., Vu, G.T., Hung, E.K., Bidwell, C.S., Bencic, T., and Breer, M.D., 

"Progress in Measuring Water Impingement Characteristics on Aircraft Surfaces," 

AIAA Paper 98–0488, January 1998. 

51. Wright, W.B. and Potapczuk, M.G, “Computational Simulation of Large Droplet 

Icing,” NASA Contractor Report, May, 1996. 

NASA/TM—2002-211700 429
52. Mundo, C., Sommerfeld, M., and Tropea, C., “Droplet-Wall Collisions: 

Experimental Studies of the deformation and Breakup Process,” International 

Journal Multiphase Flow, Vol. 21, No. 2, pp.151–173, 1995. 

53. Mundo, C., Sommerfeld, M., and Tropea, C., “On the Modeling of Liquid Sprays 

Impinging on Surfaces,” Atomization and Sprays, vol. 8, pp. 625–652, 1998. 

54. Tan J.S.C., “Droplet Dynamics – An experimental and Numerical Study,” Large 

Droplet Splashing research Workshop, DERA, England, UK, October 18, 2000. 

NASA/TM—2002-211700 430
This publication is available from the NASA Center for AeroSpace Information, 301–621–0390.

REPORT DOCUMENTATION PAGE

2. REPORT DATE

19. SECURITY CLASSIFICATION

 OF ABSTRACT

18. SECURITY CLASSIFICATION

 OF THIS PAGE

Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources,

gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this

collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson

Davis Highway, Suite 1204, Arlington, VA 22202-4302, and to the Office of Management and Budget, Paperwork Reduction Project (0704-0188), Washington, DC 20503.

NSN 7540-01-280-5500 Standard Form 298 (Rev. 2-89)

Prescribed by ANSI Std. Z39-18

298-102

Form Approved

OMB No. 0704-0188

12b. DISTRIBUTION CODE

8. PERFORMING ORGANIZATION

 REPORT NUMBER

5. FUNDING NUMBERS

3. REPORT TYPE AND DATES COVERED

4. TITLE AND SUBTITLE

6. AUTHOR(S)

7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)

11. SUPPLEMENTARY NOTES

12a. DISTRIBUTION/AVAILABILITY STATEMENT

13. ABSTRACT (Maximum 200 words)

14. SUBJECT TERMS

17. SECURITY CLASSIFICATION

 OF REPORT

16. PRICE CODE

15. NUMBER OF PAGES

20. LIMITATION OF ABSTRACT

Unclassified Unclassified

Technical Memorandum

Unclassified

National Aeronautics and Space Administration

John H. Glenn Research Center at Lewis Field

Cleveland, Ohio 44135–3191

1. AGENCY USE ONLY (Leave blank)

10. SPONSORING/MONITORING

 AGENCY REPORT NUMBER

9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)

National Aeronautics and Space Administration

Washington, DC 20546–0001

Available electronically at http://gltrs.grc.nasa.gov

October 2002

NASA TM—2002-211700

E–13444

WU–708–20–13–00

439

Experimental Investigation of Water Droplet Impingement on Airfoils, Finite

Wings, and an S-Duct Engine Inlet

Michael Papadakis, Kuohsing E. Hung, Giao T. Vu, Hsiung Wei Yeong,

Colin S. Bidwell, Marlin D. Breer, and Timothy J. Bencic

Aircraft icing; Aircraft safety; Flight safety; Ice prevention; Deicing; Impingement;

Airfoils; Wings; Swept wings; Wing flaps; Engine inlets

Unclassified -Unlimited

Subject Categories: 03 and 34 Distribution: Nonstandard

Michael Papadakis, Kuohsing E. Hung, and Hsiung Wei Yeong, Wichita State University, Wichita, Kansas 67260; Giao T.

Vu and Marlin D. Breer, Boeing Airplane Company, Wichita, Kansas 67277; Colin S. Bidwell and Timothy J. Bencic,

NASA Glenn Research Center. Responsible person, Colin S. Bidwell, organization code 5840, 216–433–3947.

Validation of trajectory computer codes, for icing analysis, requires experimental water droplet impingement data for a wide range of aircraft geometries

as well as flow and icing conditions. This report presents improved experimental and data reduction methods for obtaining water droplet impingement

data and provides a comprehensive water droplet impingement database for a range of test geometries including an MS(1)-0317 airfoil, a GLC-305

airfoil, an NACA 652-415 airfoil, a commercial transport tail section, a 36-inch chord natural laminar flow NLF(1)-0414 airfoil, a 48-inch NLF(1)-0414

section with a 25 percent chord simple flap, a state-of-the-art three-element high lift system, a NACA 64A008 finite span swept business jet tail, a fullscale business jet horizontal tail section, a 25 percent-scale business jet empennage, and an S-duct turboprop engine inlet. The experimental results were

obtained at the NASA Glenn Icing Research Tunnel (IRT) for spray clouds with median volumetric diameter (MVD) of 11, 11.5, 21, 92, and 94 microns

and for a range of angles of attack. The majority of the impingement experiments were conducted at an air speed of 175 mph corresponding to a

Reynolds number of approximately 1.6 million per foot. The maximum difference of repeated tests from the average ranged from 0.24 to 12 percent for

most of the experimental results presented. This represents a significant improvement in test repeatability compared to previous experimental studies.

The increase in test repeatability was attributed to improvements made to the experimental and data reduction methods. Computations performed with

the LEWICE-2D and LEWICE-3D computer codes for all test configurations are presented in this report. For the test cases involving median volumetric

diameters of 11 and 21 microns, the correlation between the analytical and experimental impingement efficiency distributions was good. For the median

volumetric diameters of 92 and 94-micron cases, however, the analysis produced higher impingement efficiencies and larger impingement limits than the

experiment. It is speculated that this discrepancy is due to droplet splashing and breakup experienced by large droplets during impingement.