Christine Pastor-Barsi and E. Allen Arrington

Sierra-Lobo, Inc., Cleveland, Ohio

Aero-Thermal Calibration of the NASA Glenn

Icing Research Tunnel (2012 Tests)

NASA/CR—2013-217812

March 2013
NASA STI Program . . . in Profi le

Since its founding, NASA has been dedicated to the 

advancement of aeronautics and space science. The 

NASA Scientifi c and Technical Information (STI) 

program plays a key part in helping NASA maintain 

this important role.

The NASA STI Program operates under the auspices 

of the Agency Chief Information Offi cer. It collects, 

organizes, provides for archiving, and disseminates 

NASA’s STI. The NASA STI program provides access 

to the NASA Aeronautics and Space Database and 

its public interface, the NASA Technical Reports 

Server, thus providing one of the largest collections 

of aeronautical and space science STI in the world. 

Results are published in both non-NASA channels 

and by NASA in the NASA STI Report Series, which 

includes the following report types:

• TECHNICAL PUBLICATION. Reports of 

completed research or a major signifi cant phase 

of research that present the results of NASA 

programs and include extensive data or theoretical 

analysis. Includes compilations of signifi cant 

scientifi c and technical data and information 

deemed to be of continuing reference value. 

NASA counterpart of peer-reviewed formal 

professional papers but has less stringent 

limitations on manuscript length and extent of 

graphic presentations.

• TECHNICAL MEMORANDUM. Scientifi c 

and technical fi ndings 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. Scientifi c and 

technical fi ndings by NASA-sponsored 

contractors and grantees.

• CONFERENCE PUBLICATION. Collected 

papers from scientifi c and technical 

conferences, symposia, seminars, or other 

meetings sponsored or cosponsored by NASA.

• SPECIAL PUBLICATION. Scientifi c, 

technical, or historical information from 

NASA programs, projects, and missions, often 

concerned with subjects having substantial 

public interest.

• TECHNICAL TRANSLATION. Englishlanguage translations of foreign scientifi c and 

technical material pertinent to NASA’s mission.

Specialized services also include creating custom 

thesauri, building customized databases, organizing 

and publishing research results.

For more information about the NASA STI 

program, see the following:

• Access the NASA STI program home page at 

http://www.sti.nasa.gov

• E-mail your question to help@sti.nasa.gov

• Fax your question to the NASA STI 

Information Desk at 443–757–5803

• Phone the NASA STI Information Desk at

 443–757–5802

• Write to:

 STI Information Desk

 NASA Center for AeroSpace Information

 7115 Standard Drive

 Hanover, MD 21076–1320
Christine Pastor-Barsi and E. Allen Arrington

Sierra-Lobo, Inc., Cleveland, Ohio

Aero-Thermal Calibration of the NASA Glenn

Icing Research Tunnel (2012 Tests)

NASA/CR—2013-217812

March 2013

National Aeronautics and

Space Administration

Glenn Research Center

Cleveland, Ohio 44135

Prepared under Contract NNC05CA95C
Available from

NASA Center for Aerospace Information

7115 Standard Drive

Hanover, MD 21076–1320

National Technical Information Service

5301 Shawnee Road

Alexandria, VA 22312

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

Trade names and trademarks are used in this report for identifi cation 

only. Their usage does not constitute an offi cial endorsement, 

either expressed or implied, by the National Aeronautics and 

Space Administration.

Level of Review: This material has been technically reviewed by NASA technical management OR expert reviewer(s).
Contents

Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

Nomenclature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3

Symbols . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3

Subscripts ..................................... 3

Description of Facility . ................................ 4

Test Hardware, Instrumentation and Data Systems . . . . . . . . . . . . . . . . . 5

9-Foot Survey Rake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

2D Resistive Temperature Detector (RTD) Array . . . . . . . . . . . . . . . 6

Facility Instrumentation ............................. 7

Steady-State Data Acquisition System . . . . . . . . . . . . . . . . . . . . . 8

Hot-wire Survey Rake and Instrumentation . . . . . . . . . . . . . . . . . . . 9

Quick-Check Rake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

Procedures and Test Matrix . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

Test Matrix . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

Data Reduction and Analysis . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

Facility Calculations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

9-Foot Survey Rake Calculations . . . . . . . . . . . . . . . . . . . . . . . . 14

Flow Angularity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

Turbulence Intensity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2D RTD Array Calculations . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

Discussion of Results . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

Pressure Discrepancy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

Aero-Thermal Calibration Curves . . . . . . . . . . . . . . . . . . . . . . . . 17

Flow Quality Goals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

Turbulence Intensity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

Flow Angularity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

Mach Number . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

Total Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

Static Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

Total Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

Test section to D-corner comparison . . . . . . . . . . . . . . . . . . . 23

Study around 0◦C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

Summary of Test Results . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

Recommendations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

NASA/CR—2013-217812 iii
List of Figures

Figure 1 – Schematic of the NASA Glenn Icing Research Tunnel .......... 4

Figure 2 – (a)previous flat-panel heat exchanger, (b)current chevron-design heat

exchanger . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

Figure 3 – The 9-foot horizontal survey rake installed at vertical centerline in the

IRT test section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

Figure 4 – The 9-foot horizontal survey rake installed at vertical centerline in the

IRT test section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

Figure 5 – Hemispherical head probe total pressure ports. (A-A) total pressure

port detail, (B-B) static pressure port detail. . . . . . . . . . . . . . . . . . 7

Figure 6 – RTD Array installed in the IRT test section. (a) View looking downstream. (b) View looking upstream. . . . . . . . . . . . . . . . . . . . . . . 7

Figure 7 – Grid arrangement of the 7x7 RTDs . . . . . . . . . . . . . . . . . . . . 8

Figure 8 – Details of the 2D RTD survey array probes (dimensions are in inches) 8

Figure 9 – RTD Array vertical member cross section . . . . . . . . . . . . . . . . 9

Figure 10– Arrangement of RTD Probes mounted on the D-corner turning vanes . 9

Figure 11– Hot-wire/film anemometry system: (a) NI DAQ and IFA-100 (b) hotwire rake installed in the IRT test section with five hot-wires and a pitotstatic probe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

Figure 12– Quick-check rake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

Figure 13– (a)The pipe exiting the balance chamber of the IRT and the joint at

which the 90 degree elbow was disconnected. (b)The 90 degree elbow as

installed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

Figure 14– Mach number calibration for the IRT from the 2012 full aero-thermal

calibration. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

Figure 15– Static pressure calibration for the IRT from the 2012 full aero-thermal

calibration. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

Figure 16– Total temperature calibration for the IRT from the 2012 full aerothermal calibration. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

Figure 17– IRT Turbulence Intensity, Historical Comparison at horizontal and vertical centerline, Pair = 0psig. . . . . . . . . . . . . . . . . . . . . . . . . . . 20

Figure 18– Test section turbulence intensity, as collected by the hot wire/film survey

rake. (a) Uts = 50 knots, Pair = 0 psig. (b) Uts = 50 knots, Pair = 30 psig.

(c) Uts = 50 knots, Pair = 60 psig. . . . . . . . . . . . . . . . . . . . . . . 26

Figure 18– (d) Uts = 90 knots, Pair = 0 psig. (e) Uts = 90 knots, Pair = 30 psig.

(f) Uts = 90 knots, Pair = 60 psig. . . . . . . . . . . . . . . . . . . . . . . . 26

Figure 18– (g) Uts = 120 knots, Pair = 0 psig. (h) Uts = 120 knots, Pair = 30 psig.

(i) Uts = 120 knots, Pair = 60 psig. . . . . . . . . . . . . . . . . . . . . . . 27

Figure 18– (j) Uts = 150 knots, Pair = 0 psig. (k) Uts = 150 knots, Pair = 30 psig.

(l) Uts = 150 knots, Pair = 60 psig. . . . . . . . . . . . . . . . . . . . . . . 27

Figure 18– (m) Uts = 170 knots, Pair = 0 psig. (n) Uts = 170 knots, Pair = 30 psig.

(o) Uts = 170 knots, Pair = 60 psig. . . . . . . . . . . . . . . . . . . . . . . 28

Figure 19– (a) Uts = 50 knots, Pair = 0 psig. (b) Uts = 90 knots, Pair = 0 psig. (c)

Uts = 120 knots, Pair = 0 psig. (d) Uts = 150 knots, Pair = 0 psig. . . . . . 29

NASA/CR—2013-217812 iv
Figure 19– (e) Uts = 170 knots, Pair = 0 psig. (f) Uts = 200 knots, Pair = 0 psig.

(g) Uts = 250 knots, Pair = 0 psig. . . . . . . . . . . . . . . . . . . . . . . 30

Figure 19– (i) Uts = 50 knots, Pair = 30 psig. (j) Uts = 90 knots, Pair = 30 psig.

(k) Uts = 120 knots, Pair = 30 psig. (l) Uts = 150 knots, Pair = 30 psig. . . 31

Figure 19– (m) Uts = 170 knots, Pair = 30 psig. (n) Uts = 200 knots, Pair = 30

psig. (o) Uts = 250 knots, Pair = 30 psig. . . . . . . . . . . . . . . . . . . . 32

Figure 19– (q) Uts = 50 knots, Pair = 60 psig. (r) Uts = 90 knots, Pair = 60 psig.

(s) Uts = 120 knots, Pair = 60 psig. (t) Uts = 150 knots, Pair = 60 psig. . . 33

Figure 19– (u) Uts = 170 knots, Pair = 60 psig. (v) Uts = 200 knots, Pair = 60 psig.

(w) Uts = 250 knots, Pair = 60 psig. . . . . . . . . . . . . . . . . . . . . . 34

Figure 20– Mach number distribution data from the IRT test section. Data collected using the 9-ft survey rake mounted at 9 vertical positions over several

tunnel runs. The test section Mach number data was normalized using the

bellmouth Mach number measurement. Approximate Mach number delta

is indicated for each test section setting. (a) Uts = 50 knots, Pair = 0 psig.

(b) Uts = 90 knots, Pair = 0 psig. (c) Uts = 120 knots, Pair = 0 psig. (d)

Uts = 150 knots, Pair = 0 psig. . . . . . . . . . . . . . . . . . . . . . . . . 35

Figure 20– (e) Uts = 170 knots, Pair = 0 psig. (f) Uts = 200 knots, Pair = 0 psig.

(g) Uts = 250 knots, Pair = 0 psig. . . . . . . . . . . . . . . . . . . . . . . 36

Figure 20– (i) Uts = 50 knots, Pair = 30 psig. (j) Uts = 90 knots, Pair = 30 psig.

(k) Uts = 120 knots, Pair = 30 psig. (l) Uts = 150 knots, Pair = 30 psig. . . 37

Figure 20– (m) Uts = 170 knots, Pair = 30 psig. (n) Uts = 200 knots, Pair = 30

psig. (o) Uts = 250 knots, Pair = 30 psig. . . . . . . . . . . . . . . . . . . . 38

Figure 20– (q) Uts = 50 knots, Pair = 60 psig. (r) Uts = 90 knots, Pair = 60 psig.

(s) Uts = 120 knots, Pair = 60 psig. (t) Uts = 150 knots, Pair = 60 psig. . . 39

Figure 20– (u) Uts = 170 knots, Pair = 60 psig. (v) Uts = 200 knots, Pair = 60

psig. (w) Uts = 250 knots, Pair = 60 psig. . . . . . . . . . . . . . . . . . . 40

Figure 21– Total pressure distribution data from the IRT test section. Data collected using the 9-ft survey rake mounted at 9 vertical positions over several

tunnel runs. The test section total pressure data is normalized using the

bellmouth total pressure measurement. (a) Uts = 50 knots, Pair = 0 psig.

(b) Uts = 90 knots, Pair = 0 psig. (c) Uts = 120 knots, Pair = 0 psig. (d)

Uts = 150 knots, Pair = 0 psig. . . . . . . . . . . . . . . . . . . . . . . . . 41

Figure 21– (e) Uts = 170 knots, Pair = 0 psig. (f) Uts = 200 knots, Pair = 0 psig.

(g) Uts = 250 knots, Pair = 0 psig. . . . . . . . . . . . . . . . . . . . . . . 42

Figure 21– (i) Uts = 50 knots, Pair = 30 psig. (j) Uts = 90 knots, Pair = 30 psig.

(k) Uts = 120 knots, Pair = 30 psig. (l) Uts = 150 knots, Pair = 30 psig. . . 43

Figure 21– (m) Uts = 170 knots, Pair = 30 psig. (n) Uts = 200 knots, Pair = 30

psig. (o) Uts = 250 knots, Pair = 30 psig. . . . . . . . . . . . . . . . . . . . 44

Figure 21– (q) Uts = 50 knots, Pair = 60 psig. (r) Uts = 90 knots, Pair = 60 psig.

(s) Uts = 120 knots, Pair = 60 psig. (t) Uts = 150 knots, Pair = 60 psig. . . 45

Figure 21– (u) Uts = 170 knots, Pair = 60 psig. (v) Uts = 200 knots, Pair = 60

psig. (w) Uts = 250 knots, Pair = 60 psig. . . . . . . . . . . . . . . . . . . 46

NASA/CR—2013-217812 v
Figure 22– Static pressure distribution data from the IRT test section. Data collected using the 9-ft survey rake mounted at 9 vertical positions over several

tunnel runs. (a) Uts = 50 knots, Pair = 0 psig. (b) Uts = 90 knots, Pair =

0 psig. (c) Uts = 120 knots, Pair = 0 psig. (d) Uts = 150 knots, Pair = 0 psig. 47

Figure 22– (e) Uts = 170 knots, Pair = 0 psig. (f) Uts = 200 knots, Pair = 0 psig.

(g) Uts = 250 knots, Pair = 0 psig. . . . . . . . . . . . . . . . . . . . . . . 48

Figure 22– (i) Uts = 50 knots, Pair = 30 psig. (j) Uts = 90 knots, Pair = 30 psig.

(k) Uts = 120 knots, Pair = 30 psig. (l) Uts = 150 knots, Pair = 30 psig. . . 49

Figure 22– (m) Uts = 170 knots, Pair = 30 psig. (n) Uts = 200 knots, Pair = 30

psig. (o) Uts = 250 knots, Pair = 30 psig. . . . . . . . . . . . . . . . . . . . 50

Figure 22– (q) Uts = 50 knots, Pair = 60 psig. (r) Uts = 90 knots, Pair = 60 psig.

(s) Uts = 120 knots, Pair = 60 psig. (t) Uts = 150 knots, Pair = 60 psig. . . 51

Figure 22– (u) Uts = 170 knots, Pair = 60 psig. (v) Uts = 200 knots, Pair = 60

psig. (w) Uts = 250 knots, Pair = 60 psig. . . . . . . . . . . . . . . . . . . 52

Figure 23– Total Temperature test section temperature distribution, as collected

by the 2D RTD survey array. (a) Uts = 217 knots, TT,davg = 5.0◦C, Pair =

0 psig (b) Uts = 217 knots, TT,davg = 5.0◦C, Pair = 30 psig (c) Uts = 217

knots, TT,davg = 5.0◦C, Pair = 60 psig . . . . . . . . . . . . . . . . . . . . . 53

Figure 23– (d) Uts = 50 knots, TT,davg = 3.6◦C, Pair = 0 psig, (e) Uts = 50 knots,

TT,davg = 3.6◦C, Pair = 30 psig (f) Uts = 50 knots, TT,davg = 3.6◦C, Pair =

60 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54

Figure 23– (g) Uts = 130 knots, TT,davg = 3.9◦C, Pair = 0 psig (h) Uts = 130 knots,

TT,davg = 3.9◦C, Pair = 30 psig (i) Uts = 130 knots, TT,davg = 3.9◦C, Pair =

60 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55

Figure 23– (j) Uts = 300 knots, TT,davg = 6.3◦C, Pair = 0 psig (k) Uts = 300 knots,

TT,davg = 6.4◦C, Pair = 30 psig (l) Uts = 300 knots, TT,davg = 6.4◦C, Pair =

60 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56

Figure 23– (m) Uts = 220 knots, TT,davg = 3.0◦C, Pair = 30 psig (n) Uts = 130

knots, TT,davg = 2.1◦C, Pair = 30 psig (o) Uts = 220 knots, TT,davg = 2.0◦C,

Pair = 30 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

Figure 23– (p) Uts = 130 knots, TT,davg = 1.0◦C, Pair = 30 psig (q) Uts = 220 knots,

TT,davg = 1.0◦C, Pair = 30 psig (r) Uts = 130 knots, TT,davg = 0.0◦C, Pair =

30 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58

Figure 23– (s) Uts = 220 knots, TT,davg = 0.0◦C, Pair = 0 psig (t) Uts = 220 knots,

TT,davg = 0.0◦C, Pair = 30 psig (u) Uts = 220 knots, TT,davg = 0.0◦C, Pair =

60 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59

Figure 23– (v) Uts = 50 knots, TT,davg = -1.5◦C, Pair = 0 psig (w) Uts = 50 knots,

TT,davg = -1.5◦C, Pair = 30 psig (x) Uts = 50 knots, TT,davg = -1.5◦C, Pair

= 60 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60

Figure 23– (y) Uts = 130 knots, TT,davg = -1.1◦C, Pair = 0 psig (z) Uts = 130 knots,

TT,davg = -1.1◦C, Pair = 30 psig (aa) Uts = 130 knots, TT,davg = -1.1◦C, Pair

= 60 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61

Figure 23– (bb) Uts = 220 knots, TT,davg = -15.1◦C, Pair = 0 psig (cc) Uts = 220

knots, TT,davg = -15.1◦C, Pair = 30 psig (dd) Uts = 220 knots, TT,davg =

-15.1◦C, Pair = 60 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62

NASA/CR—2013-217812 vi
Figure 23– (ee) Uts = 50 knots, TT,davg = -16.9◦C, Pair = 0 psig (ff) Uts = 50 knots,

TT,davg = -16.9◦C, Pair = 30 psig (gg) Uts = 50 knots, TT,davg = -16.9◦C,

Pair = 60 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63

Figure 23– (hh) Uts = 130 knots, TT,davg = -16.4◦C, Pair = 0 psig (ii) Uts = 130

knots, TT,davg = -16.4◦C, Pair = 30 psig (jj) Uts = 130 knots, TT,davg =

-16.4◦C, Pair = 60 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64

Figure 23– (kk) Uts = 300 knots, TT,davg = -13.6◦C, Pair = 0 psig (ll) Uts = 300

knots, TT,davg = -13.6◦C, Pair = 30 psig (mm) Uts = 300 knots, TT,davg =

-13.6◦C, Pair = 60 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65

Figure 23– (nn) Uts = 220 knots, TT,davg = -30.0◦C, Pair = 0 psig (oo) Uts = 220

knots, TT,davg = -30.0◦C, Pair = 30 psig (pp) Uts = 220 knots, TT,davg =

-30.0◦C, Pair = 60 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

Figure 23– (qq) Uts = 50 knots, TT,davg = -33.3◦C, Pair = 0 psig (rr) Uts = 50 knots,

TT,davg = -33.3◦C, Pair = 30 psig (ss) Uts = 50 knots, TT,davg = -33.3◦C, Pair

= 60 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 67

Figure 23– (tt) Uts = 130 knots, TT,davg = -32.6◦C, Pair = 0 psig (uu) Uts = 130

knots, TT,davg = -32.6◦C, Pair = 30 psig (vv) Uts = 130 knots, TT,davg =

-32.6◦C, Pair = 60 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68

Figure 23– (ww) Uts = 300 knots, TT,davg = -28.2◦C, Pair = 0 psig (xx) Uts = 300

knots, TT,davg = -28.0◦C, Pair = 30 psig (yy) Uts = 300 knots, TT,davg =

-28.0◦C, Pair = 60 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69

Figure 23– (zz) Uts = 220 knots, TT,davg = -30.7◦C, Pair = 30 psi (aaa) Uts = 130

knots, TT,davg = -32.7◦C, Pair = 30 psig . . . . . . . . . . . . . . . . . . . . 70

Figure 23– (bbb) Uts = 220 knots, TT,davg = -14.9◦C, Pair = 30 psig (ccc) Uts =

130 knots, TT,davg = -15.7◦C, Pair = 30 psig . . . . . . . . . . . . . . . . . 71

Figure 23– (ddd) Uts = 220 knots, TT,davg = -3.1◦C, Pair = 30 psig (eee) Uts = 130

knots, TT,davg = -3.7◦C, Pair = 30 psig . . . . . . . . . . . . . . . . . . . . 72

Figure 23– (fff) Uts = 220 knots, TT,davg = -1.8◦C, Pair = 30 psig (ggg) Uts = 130

knots, TT,davg = -2.7◦C, Pair = 30 psig . . . . . . . . . . . . . . . . . . . . 73

Figure 23– (hhh) Uts = 220 knots, TT,davg = -0.8◦C, Pair = 30 psig (iii) Uts = 130

knots, TT,davg = -1.7◦C, Pair = 30 psig . . . . . . . . . . . . . . . . . . . . 74

Figure 24– Test section versus D-corner surface plots (a) Vknots = 200 knots, TT,davg

= 7◦C, Pair = 0 psig . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 75

Figure 24– (b) Vknots = 150 knots, TT,davg = 6◦C, Pair = 0 psig . . . . . . . . . . . 75

Figure 24– (c) Vknots = 100 knots, TT,davg = 6◦C, Pair = 0 psig . . . . . . . . . . . 76

Figure 24– (d) Vknots = 50 knots, TT,davg = 6◦C, Pair = 0 psig . . . . . . . . . . . 76

Figure 24– (e) Vknots = 220 knots, TT,davg = 5◦C, Pair = 0 psig . . . . . . . . . . . 77

Figure 24– (f) Vknots = 220 knots, TT,davg = 5◦C, Pair = 60 psig . . . . . . . . . . 77

Figure 24– (g) Vknots = 220 knots, TT,davg = 5◦C, Pair = 30 psig . . . . . . . . . . 78

Figure 24– (h) Vknots = 50 knots, TT,davg = 4◦C, Pair = 0 psig . . . . . . . . . . . 78

Figure 24– (i) Vknots = 50 knots, TT,davg = 4◦C, Pair = 60 psig . . . . . . . . . . . 79

Figure 24– (j) Vknots = 50 knots, TT,davg = 4◦C, Pair = 30 psig . . . . . . . . . . . 79

Figure 24– (k) Vknots = 130 knots, TT,davg = 4◦C, Pair = 0 psig . . . . . . . . . . . 80

Figure 24– (l) Vknots = 130 knots, TT,davg = 4◦C, Pair = 60 psig . . . . . . . . . . 80

Figure 24– (m) Vknots = 130 knots, TT,davg = 4◦C, Pair = 30 psig . . . . . . . . . . 81

NASA/CR—2013-217812 vii
Figure 24– (n) Vknots = 300 knots, TT,davg = 6◦C, Pair = 0 psig . . . . . . . . . . . 81

Figure 24– (o) Vknots = 300 knots, TT,davg = 6◦C, Pair = 60 psig . . . . . . . . . . 82

Figure 24– (p) Vknots = 300 knots, TT,davg = 6◦C, Pair = 30 psig . . . . . . . . . . 82

Figure 24– (q) Vknots = 220 knots, TT,davg = 3◦C, Pair = 30 psig . . . . . . . . . . 83

Figure 24– (r) Vknots = 130 knots, TT,davg = 2◦C, Pair = 30 psig . . . . . . . . . . 83

Figure 24– (s) Vknots = 220 knots, TT,davg = 2◦C, Pair = 30 psig . . . . . . . . . . 84

Figure 24– (t) Vknots = 130 knots, TT,davg = 1◦C, Pair = 30 psig . . . . . . . . . . 84

Figure 24– (u) Vknots = 220 knots, TT,davg = 1◦C, Pair = 30 psig . . . . . . . . . . 85

Figure 24– (v) Vknots = 130 knots, TT,davg = 0◦C, Pair = 30 psig . . . . . . . . . . 85

Figure 24– (w) Vknots = 220 knots, TT,davg = 0◦C, Pair = 0 psig . . . . . . . . . . 86

Figure 24– (x) Vknots = 220 knots, TT,davg = 0◦C, Pair = 60 psig . . . . . . . . . . 86

Figure 24– (y) Vknots = 220 knots, TT,davg = 0◦C, Pair = 30 psig . . . . . . . . . . 87

Figure 24– (z) Vknots = 50 knots, TT,davg = -2◦C, Pair = 0 psig . . . . . . . . . . . 87

Figure 24– (aa) Vknots = 50 knots, TT,davg = -2◦C, Pair = 60 psig . . . . . . . . . 88

Figure 24– (bb) Vknots = 50 knots, TT,davg = -2◦C, Pair = 30 psig . . . . . . . . . 88

Figure 24– (cc) Vknots = 130 knots, TT,davg = -1◦C, Pair = 0 psig . . . . . . . . . 89

Figure 24– (dd) Vknots = 130 knots, TT,davg = -1◦C, Pair = 60 psig . . . . . . . . 89

Figure 24– (ee) Vknots = 130 knots, TT,davg = -1◦C, Pair = 30 psig . . . . . . . . . 90

Figure 24– (ff) Vknots = 300 knots, TT,davg = 1◦C, Pair = 0 psig . . . . . . . . . . 90

Figure 24– (gg) Vknots = 300 knots, TT,davg = 1◦C, Pair = 60 psig . . . . . . . . . 91

Figure 24– (hh) Vknots = 300 knots, TT,davg = 1◦C, Pair = 30 psig . . . . . . . . . 91

Figure 24– (ii) Vknots = 220 knots, TT,davg = -15◦C, Pair = 0 psig . . . . . . . . . 92

Figure 24– (jj) Vknots = 220 knots, TT,davg = -15◦C, Pair = 60 psig . . . . . . . . 92

Figure 24– (kk) Vknots = 220 knots, TT,davg = -15◦C, Pair = 30 psig . . . . . . . . 93

Figure 24– (ll) Vknots = 50 knots, TT,davg = -17◦C, Pair = 0 psig . . . . . . . . . . 93

Figure 24– (mm) Vknots = 50 knots, TT,davg = -17◦C, Pair = 60 psig . . . . . . . . 94

Figure 24– (nn) Vknots = 50 knots, TT,davg = -17◦C, Pair = 30 psig . . . . . . . . 94

Figure 24– (oo) Vknots = 130 knots, TT,davg = -16◦C, Pair = 0 psig . . . . . . . . . 95

Figure 24– (pp) Vknots = 130 knots, TT,davg = -16◦C, Pair = 60 psig . . . . . . . . 95

Figure 24– (qq) Vknots = 130 knots, TT,davg = -16◦C, Pair = 30 psig . . . . . . . . 96

Figure 24– (rr) Vknots = 300 knots, TT,davg = -14◦C, Pair = 0 psig . . . . . . . . . 96

Figure 24– (ss) Vknots = 300 knots, TT,davg = -14◦C, Pair = 60 psig . . . . . . . . 97

Figure 24– (tt) Vknots = 300 knots, TT,davg = -14◦C, Pair = 30 psig . . . . . . . . 97

Figure 24– (uu) Vknots = 220 knots, TT,davg = -30◦C, Pair = 0 psig . . . . . . . . 98

Figure 24– (vv) Vknots = 220 knots, TT,davg = -30◦C, Pair = 60 psig . . . . . . . . 99

Figure 24– (ww) Vknots = 220 knots, TT,davg = -30◦C, Pair = 30 psig . . . . . . . 99

Figure 24– (xx) Vknots = 50 knots, TT,davg = -33◦C, Pair = 0 psig . . . . . . . . . 100

Figure 24– (yy) Vknots = 50 knots, TT,davg = -33◦C, Pair = 60 psig . . . . . . . . . 100

Figure 24– (zz) Vknots = 50 knots, TT,davg = -33◦C, Pair = 30 psig . . . . . . . . . 101

Figure 24– (aaa) Vknots = 130 knots, TT,davg = -33◦C, Pair = 0 psig . . . . . . . . 101

Figure 24– (bbb) Vknots = 130 knots, TT,davg = -33◦C, Pair = 60 psig . . . . . . . 102

Figure 24– (ccc) Vknots = 130 knots, TT,davg = -33◦C, Pair = 30 psig . . . . . . . . 102

Figure 24– (ddd) Vknots = 300 knots, TT,davg = -28◦C, Pair = 0 psig . . . . . . . . 103

Figure 24– (eee) Vknots = 300 knots, TT,davg = -28◦C, Pair = 60 psig . . . . . . . . 103

Figure 24– (fff) Vknots = 300 knots, TT,davg = -28◦C, Pair = 30 psig . . . . . . . . 104

NASA/CR—2013-217812 viii
Figure 24– (ggg) Vknots = 220 knots, TT,davg = -31◦C, Pair = 30 psig . . . . . . . 104

Figure 24– (hhh) Vknots = 130 knots, TT,davg = -33◦C, Pair = 30 psig . . . . . . . 105

Figure 24– (iii) Vknots = 220 knots, TT,davg = -15◦C, Pair = 30 psig . . . . . . . . 105

Figure 24– (jjj) Vknots = 130 knots, TT,davg = -16◦C, Pair = 30 psig . . . . . . . . 106

Figure 24– (kkk) Vknots = 220 knots, TT,davg = -3◦C, Pair = 30 psig . . . . . . . . 106

Figure 24– (lll) Vknots = 130 knots, TT,davg = -4◦C, Pair = 30 psig . . . . . . . . . 107

Figure 24– (mmm) Vknots = 220 knots, TT,davg = -2◦C, Pair = 30 psig . . . . . . . 107

Figure 24– (nnn) Vknots = 130 knots, TT,davg = -3◦C, Pair = 30 psig . . . . . . . . 108

Figure 24– (ooo) Vknots = 220 knots, TT,davg = -1◦C, Pair = 30 psig . . . . . . . . 108

Figure 24– (ppp) Vknots = 130 knots, TT,davg = -2◦C, Pair = 30 psig . . . . . . . . 109

NASA/CR—2013-217812 ix
List of Tables

Table 1 – Test matrix for the 9-ft survey rake. . . . . . . . . . . . . . . . . . . . . 11

Table 2 – Test matrix for the RTD Array. . . . . . . . . . . . . . . . . . . . . . . 12

Table 3 – Test matrix for the hot-wire survey rake. . . . . . . . . . . . . . . . . . 12

Table 4 – Test matrix for the quick-check rake. . . . . . . . . . . . . . . . . . . . 12

Table 5 – Aero-thermal flow quality goals for an icing tunnel test section. . . . . . 19

Table 6 – Turbulence Intensity Test Section Spatial Uniformity . . . . . . . . . . 20

Table 7 – Flow Angularity Test Section Spatial Uniformity . . . . . . . . . . . . . 21

Table 8 – Airspeed Test Section Spatial Uniformity . . . . . . . . . . . . . . . . . 22

Table 9 – Temperature Test Section Spatial Uniformity . . . . . . . . . . . . . . . 23

NASA/CR—2013-217812 x
Aero-Thermal Calibration of the NASA Glenn Icing

Research Tunnel (2012 Tests)

Summary

A full aero-thermal calibration of the NASA Glenn Icing Research Tunnel (IRT) was

completed in 2012 following the major modifications to the facility that included replacement

of the refrigeration plant and heat exchanger. The calibration test provided data used to fully

document the aero-thermal flow quality in the IRT test section and to construct calibration

curves for the operation of the IRT.

Introduction

Updating and maintaining the icing cloud calibration, aero-thermal calibration and flow

quality data are critical tasks in the NASA Glenn Icing Research Tunnel (IRT). Establishing

and maintaining the calibrations is the only way to ensure that correct test section operating

conditions are being set for a given set of facility control inputs. Without knowledge of

the calibration and flow quality data, it is impossible to provide high-quality test data for

customers and researchers. To ensure that the data quality from the IRT is always at

the highest standards, IRT staff and wind tunnel calibration personnel have developed and

continue to refine the calibration methodologies used.

The aero-thermal calibration test program provides the calibration relationships needed

to accurately determine the test section operating conditions for total pressure, airspeed

(comparable Mach number) and total temperature. Once these calibrated conditions are

determined, all other aero-thermal operating conditions can be calculated. In addition to

the calibration information, detailed flow quality data (spatial uniformity) is also collected.

The collected calibration and flow quality data provide a complete description of the aerothermal operation of the IRT.

The current aero-thermal calibration methodology and instrumentation has evolved based

on lessons learned by the calibration team over the past 20 years, input from IRT customers,

in-house research staff, IRT facility personnel, and recommendations from references [1] and

[2]. The SAE Standard ”Calibration and Acceptance of Icing Wind Tunnels” (reference [1])

defines a time table and level of calibration that should be conducted following modifications

to an icing tunnel. Correspondingly, the AIAA Recommended Practice ”Calibration of

Subsonic and Transonic Wind Tunnels” (reference [2]) states that short, check calibrations

should be conducted multiple times each year to ensure repeatable operation of the wind

tunnel. Based on these recommendations, the following aero-thermal calibration tests have

been defined:

• Full calibration: Includes collection of aero-thermal calibration data over the entire

operating range of the IRT as well as a complete mapping of the IRT flow quality at

Christine Pastor-Barsi and E. Allen Arrington 

Sierra Lobo, Inc. 

Fremont, Ohio 44135 

NASA/CR—2013-217812 1
one cross section of the test section, typically at the centerline of the turntable. A full

calibration should be conducted every 5 years or following a major facility modification.

The full calibration provides all of the information needed to develop the aero-thermal

calibration relationships, or calibration curves, for the facility and provides extensive

detailed information on the aero-thermal flow quality characteristics of the test section.

• Interim calibration: Includes collection of aero-thermal calibration data over the entire

operating range of the IRT, however, data is only required from the test section centerline. An interim calibration is conducted one year following a full calibration. The

interim calibration is used to validate the data collected during the full calibration,

therefore, if the full calibration and interim calibration data match then the facility is

operating properly, however if not, then an investigation must commence immediately

to rectify the discrepancies.

• Check calibration: A one-day test using a very simple rake. Check calibration testing

covers the entire operating range and typically lasts one day, the test matrix is not as

extensive as a full or interim calibration. This calibration should be conducted 2 to

3 times per year. The check calibration data is used in a statistical process control

analysis to monitor the stability and repeatability of the facility operation.

This paper provides a detailed description of the full aero-thermal calibration conducted

in the IRT in 2012. This calibration was required due to the major modifications to the IRT,

consisting of the replacement of the refrigeration plant and heat exchanger. The 2012 full

calibration was also needed to update the calibration curves that are used to set operating

conditions in the test section of the IRT. Previous to the 2012 calibration, the most recent

full calibration was completed in 2009 following removal of ramps in the bellmouth of the

facility (reference [3]). Additionally, an Interim calibration was completed in 2010. The

goals for the 2012 aero-thermal full calibration are listed below:

• Complete data collection and construct aero-thermal calibration curves for the IRT.

The three calibration relationships used are total pressure, Mach number and total

temperature.

• Complete detailed flow quality surveys using the 9-foot survey rake, 2-D RTD array,

hot-wire rake, and the quick-check rake.

NASA/CR—2013-217812 2
Nomenclature

Symbols

A Conductive heat transfer, hot-wire/film

B Convective heat transfer, hot-wire/film

C0, C1, C2 RTD probe total temperature flow recovery curve-fit coefficients

Cα Pitch angle pressure coefficient

Cβ Yaw angle pressure coefficient

Co Total pressure coefficient (9-foot rake pressure probes)

Cq Static pressure coefficient (9-foot rake pressure probes)

E hot-wire anemometer output voltage, volts

K0 to K2 Flow-angle prediction coefficients, degrees

l characteristic length, ft

M Mach number

N Number of data points

n coefficient, hot-wire/film

P Pressure, psia

P1 to P9 Flow-angle probe pressures, psia

Pair Spray bar air pressure, psig

Pavg Average of P1, P2, P3, and P4, psia

Prat Ratio of static to total pressure

PS Static pressure, psia (psf)

PS,rake Average of P6, P7, P8, and P9 (probe static pressure), psia

PT Total pressure, psia (psf)

PT,rake Equal to P5 (probe total pressure), psia

Q Measured velocity, hot-wire/film

q Dynamic pressure, psi

R Specific gas constant for air, 1716 f t2

(sec2◦R)

Re Reynolds number

T Temperature, ◦C(◦F)

Ts Static temperature, ◦C(◦F)

TT Total temperature, ◦C(◦F)

TT,davg Average of the 24 D-corner total temperature measurements, ◦C(◦F)

TT,d,i D-corner total temperature measurement, ◦C(◦F)

U Velocity, knots (ft/sec, mph)

X Axial coordinate, with axis origin at bellmouth/test section weld seam, inches

Y Spanwise coordinate, with axis origin at the test section inner wall, inches

Z Vertical coordinate, with axis origin at the test section floor, inches

α Pitch flow-angle, degrees

β Yaw flow-angle, degrees

γ Ratio of specific heats, 1.4

Δ Measured pitch or yaw angle offset, degrees

Subscripts

arm 6-degree-of-freedom inspection arm

NASA/CR—2013-217812 3
array 2D RTD array

avg Average

bm Tunnel bellmouth

i Data point index

j Data point index

level Digital level, inclinometer

local Test section parameters after all calibration coefficients have been included

north North bellmouth rake

rake 9-ft survey rake

ruler Ruler or tape measure

south South bellmouth rake

ts Tunnel test section

Description of Facility

A schematic of the NASA Glenn Icing Research Tunnel (IRT) is shown in Figure 1. The

IRT is a closed loop atmospheric tunnel. The test section is a 6-feet high by 9-feet wide and

20-feet in length with no divergence along any surface. The spraybars which inject atomized

water into the flow stream to create the icing conditions are located in the settling chamber

between the D-corner turning vanes and the bellmouth inlet.

Figure 1: Schematic of the NASA Glenn Icing Research Tunnel

Operational velocities of the IRT range from 25 knots to 350 knots and tunnel temperature is controllable from +20 ◦C total temperature to −40 ◦C test section static temperature.

The recently upgraded heat exchanger, from a flat-panel to a chevron-design (Figure 2),

which enables this range of temperatures is located between C and D corners on the left in

Figure 1. Additionally, the upgraded refrigeration plant is located adjacent to the tunnel

near the C-corner. Pushing airflow around the circuit is a 5000-horsepower electric motor

driving a 25-foot diameter, 12-blade wooden fan [3].

NASA/CR—2013-217812 4
Figure 2: (a)previous flat-panel heat exchanger, (b)current chevron-design heat exchanger

Test Hardware, Instrumentation and Data Systems

Several pieces of hardware are utilized to collect data during a full aero-thermal calibration

of the IRT: the 9-foot survey rake, 2D Resistive Temperature Detector (RTD) survey array,

the hot-wire survey rake, and the quick-check rake. The test hardware, instrumentation and

data systems will be described in detail in the subsequent sections.

9-Foot Survey Rake

The 9-foot survey rake (Figure 3) is used to measure total pressure, static pressure, and

angular pressure, thereby enabling calculations of velocity and flow angularity. The rake is

supported in the center with a vertical strut and at both ends by plates with a bolt pattern

which enables positioning of the rake every 6-inches above and below vertical centerline.

Additionally, the 9-ft survey rake probes are positioned at the axial center point of the

model turn table seen in Figure 4. The axial position of the rake 179.3-inches (from tunnel

station 0 to the probe tips). This has been the standard position used starting in 2004.

Figure 3 illustrates the left handed X-Y-Z coordinate system that is used with the points of

origin as follows. The origin for the X-axis is at the bellmouth to test section weld seam.

The origin for the Y-axis is the bottom of the inner wall where the wall meets the floor. The

origin for the Z-axis is at the floor where the floor meets the inner wall.

The 9-Foot survey rake pressure probes are mounted through the main structure of the

survey rake, as illustrated in Figure 5, and are nominally positioned in 9-inch increments.

The hemispherical-head, 5-hole pressure probes (Figure 5) have a single total pressure port

at the center front of the probe to measure total pressure, and 4 additional pressure ports in

90 ◦ increments around the probe head at 45 ◦ offsets to measure pitch and yaw angle of the

airflow. In addition there are 4 static pressure ports 5.75-inches downstream of the head,

at 90 ◦ increments (Figure 5). The probes were all calibrated at the NASA Glenn 3.5-inch

diameter free jet calibration facility [4].

NASA/CR—2013-217812 5
Figure 3: The 9-foot horizontal survey rake installed at vertical centerline in the IRT test

section

Figure 4: The 9-foot horizontal survey rake installed at vertical centerline in the IRT test

section

2D Resistive Temperature Detector (RTD) Array

The 2D Resistive Temperature Detector (RTD) Survey Array is a grid of RTDs, as shown

in Figure 6. The 7x7 grid positions the probes at 0%, ±25%, ±50%, and ±75% of the test

section both horizontally and vertically (Figure 7). Probes extend 7-inches forward of the

leading edge of the support members of the 2D RTD array. The probe heads are positioned

15-inches downstream of the model turn table center.

Figure 8 illustrates the details of the RTD probe that is used in the array. The total

temperature probes used in the array are 4-wire RTDs with a ceramic capsule sensor. Total

temperature recovery testing occurred in 2005 [5]. Figure 9 shows the cross section of the RTD

survey array vertical member which has a 0.75-inche channel for instrumentation wiring. It

also illustrates how the RTD probes extend 7-inches forward.

NASA/CR—2013-217812 6
Figure 5: Hemispherical head probe total pressure ports. (A-A) total pressure port detail,

(B-B) static pressure port detail.

Figure 6: RTD Array installed in the IRT test section. (a) View looking downstream. (b)

View looking upstream.

Facility Instrumentation

Standard facility instrumentation includes the north and south bellmouth pitot-static

probes and an array of RTDs in D-corner. Facility total temperature measurements were

acquired from a 24-probe array (4 rows of 6 RTD probes, Figure 10) mounted on the leading

edge of the D-corner turning vanes. The north and south pitot-static probes measure total

pressure and delta pressure, and are heated to prevent icing due to their position downstream

of the spraybars.

NASA/CR—2013-217812 7
Figure 7: Grid arrangement of the 7x7 RTDs

Figure 8: Details of the 2D RTD survey array probes (dimensions are in inches)

Steady-State Data Acquisition System

Real time steady-state data acquisition and display are provided by the IRT Escort Alpha

System. This is the standard data acquisition and data display system used in the large

test facilities at NASA Glenn. The system accommodates inputs from the Electronically

Scanned Pressure (ESP) System, the facility distributed process control system, and any

analog devices such as thermocouples, RTDs and pressure transducers. This system records

all steady-state pressures and temperatures from the standard facility instrumentation and

test specific hardware including the 9-ft survey rake, the 2D RTD survey array, and the quickcheck rake. It also records facility operational parameters such as spraybar air pressure and

drive fan speed. An Escort program was specifically written to support the aero-thermal

calibration in the IRT.

The ESP system used during the test program utilized thirty-two port, rack mounted

NASA/CR—2013-217812 8
Figure 9: RTD Array vertical member cross section

Figure 10: Arrangement of RTD Probes mounted on the D-corner turning vanes

modules. For this test program ±5 psid modules were used. The accuracy in the pressure

measurements made with the ESP System is ±0.1 percent of full-scale of the module, or

±0.005 psia for the ±5 psid modules used.

Hot-Wire Survey Rake and Instrumentation

A custom hot-wire system has been developed for use at NASA GRC and is shown in

Figure 11(a). The hot-wire or film is connected to the TSI Incorporated (Shoreview, MN)

IFA-100 Anemometer, Model 150 Transducer module. The output from the anemometer is

fed into the National Instruments (NI) Corporation (Austin, TX) Data Acquisition (DAQ)

System which is connected to a laptop with NI Labview software. A custom Labview program

was written for the hot-wire/film sensors which has the capability to accommodate up to 16

sensors across 4 PXI-6115 DAQ cards. A button trigger is connected between the hot-wire

data system and the facility steady-state data acquisition system, Escort, which enables both

systems to be triggered simultaneously.

Turbulence intensity data were acquired with the hot-wire/film survey rake shown in

11(b). The hot-wire/film was installed so as to position the wire/film horizontally or along

the Y-axis with respect to the test section. Prior to the construction of this rake the hotwires were mounted to the top of the 9-ft survey rake. Calibrations for the hot-wires/films

are performed in situ in the wind tunnel test section from minimum to maximum velocity at

the beginning of testing for each lateral position. Testing with the hot-wire rake is only done

in the incompressible regime, M < 0.3. Only single wires/films normal to the axial velocity

are used as the calibration is conducted in situ.

NASA/CR—2013-217812 9
Figure 11: Hot-wire/film anemometry system: (a) NI DAQ and IFA-100 (b) hot-wire rake

installed in the IRT test section with five hot-wires and a pitot-static probe

Quick-Check Rake

The quick-check rake was utilized on the last day of testing. Data is acquired but typically

not looked at unless an issue is found with data from other hardware. Figure 12 shows the

quick-check rake as installed in the IRT. It also shows the probe positions on the quick-check

rake.

Figure 12: Quick-check rake

NASA/CR—2013-217812 10
Procedures and Test Matrix

The IRT was operated using standard test procedures during the aero-thermal calibration.

At each test condition, two data readings were acquired. Each reading was an average of 10

scans at a rate of 1 scan per second. For the 9-ft survey rake, and the hot-wire survey rake,

prior to taking a reading, the spatial standard deviation of the D-corner RTDs was verified to

be within ±0.5 ◦C. During testing of the 2D RTD array, the spatial standard deviation was

verified to be within ±0.1 ◦C and, the temporal standard deviation of the D-corner RTDs

was verified to be within ±0.1 ◦C.

Test Matrix

Table 1 lists the data points that were acquired with the 9-ft survey rake. During testing

static temperature was held at 4.0 ◦C [1].

Table 2 summarizes the data points that were recorded for the 2D RTD Array. During

testing of the 2D RTD array, total temperature was set instead of static temperature. The

operators were then instructed to go “hands off” of the temperature controls. To allow for

a manageable total temperature swing of approximately ±5.0 ◦C, for each new sequence,

total temperature was stabilized at the target temperature, i.e. −10.0 ◦C, at 220 knots prior

to acquiring data. The data at the remaining velocities were acquired in the order of 50,

130, and 300 knots. Additionally, the spraybar air pressures were tested in the sequence of

0, 60, 30 psig. This was done so the spraybars would stabilize at their normal operating

temperature of 80 − 85 ◦C more quickly.

The hot-wire survey rake test points are illustrated in Table 3. Turbulence data were

collected at a tunnel total temperature of 7.8 ◦C to prevent the tunnel static temperature

from dropping below freezing.

Table 4 shows the data points that were acquired with the quick-check rake. It is seen

that the quick-check rake collected data at the lateral centerline position, at a subset of data

points.

Table 1: Test matrix for the 9-ft survey rake.

Rake Position Static Test Section Spraybar air pressure,

(horizontal) temperature, TT,ts ◦C Airspeed, Utsknots Pair, psig

CL 4.0 50,90,120,150,170,200,250 0,30,60

CL-6 4.0 50,90,120,150,170,200,250,300 0,30,60

CL+6 4.0 50,90,120,150,170,200,250,300 0,30,60

CL-12 4.0 50,90,120,150,170,200,250,300 0,30,60

CL+12 4.0 50,90,120,150,170,200,250,300 0,30,60

CL-18 4.0 50,90,120,150,170,200,250,300 0,30,60

CL+18 4.0 50,90,120,150,170,200,250,300 0,30,60

CL-24 4.0 50,90,120,150,170,200,250,300 0,30,60

CL+24 4.0 50,90,120,150,170,200,250,300 0,30,60

NASA/CR—2013-217812 11
Table 2: Test matrix for the RTD Array.

Test Section total Test Section Spraybar air pressure,

temperature, TT,ts ◦C Airspeed, Utsknots Pair, psig

-30 50,130,220,300 0,30,60

-20 50,130,220,300 0,30,60

-10 50,130,220,300 0,30,60

-3 50,130,220,300 0,30,60

-2 50,130,220,300 0,30,60

-1 50,130,220,300 0,30,60

0 50,130,220,300 0,30,60

1 50,130,220,300 0,30,60

2 50,130,220,300 0,30,60

3 50,130,220,300 0,30,60

5 50,130,220,300 0,30,60

Table 3: Test matrix for the hot-wire survey rake.

Rake Position Test Section total Test Section Spraybar air pressure,

(lateral) temperature, TT,ts ◦C Airspeed, Utsknots Pair, psig

CL 7.8 50,90,120,150,170 0,30,60

CL-18 7.8 50,90,120,150,170 0,30,60

CL-36 7.8 50,90,120,150,170 0,30,60

CL+18 7.8 50,90,120,150,170 0,30,60

CL+36 7.8 50,90,120,150,170 0,30,60

Table 4: Test matrix for the quick-check rake.

Rake Position Test Section Test Section Spraybar air pressure,

(lateral) Static Temperature, TT,ts ◦C Airspeed, Utsknots Pair, psig

CL 4 50, 130, 220, 300 0, 30, 60

CL -10 50, 130, 220, 300 0, 30, 60

CL -25 50, 130, 220, 300 0, 30, 60

CL -40 50, 130, 220, 300 0, 30, 60

NASA/CR—2013-217812 12
Data Reduction and Analysis

U.S. customary units of measurement are used in the following data reduction. However,

the icing community prefers a mixed set of units including airspeed in knots and temperature

in degrees Celsius ( ◦C). Therefore, the details on the data reduction are presented as they

are carried out in English units. The final results have been converted to and are presented

in the units used by the icing community.

For the following calculations, the bm subscript refers to measured or calculated parameters associated with the two bellmouth pitot-static probes. The subscript rake refers to

measured or calculated parameters associated with any of the probes on the 9-ft survey rake.

Additionally, the subscript local refers to the measured or calculated corrected rake parameters which have been corrected by individual probe calibration coefficients and represent

the true local properties in the test section. All of the local total pressures, static pressures,

and Mach numbers are normalized by bellmouth parameters to arrive at recovery ratios. All

of the equations utilized in the data reduction were compressible flow equations [6].

Facility Calculations

The bellmouth pitot-static probes in the IRT measure total pressure and delta pressure.

Equation 1 shown below calculates the average that is taken of the bellmouth total pressure

between the north and south pitot-static probes.

PT,bm = (PT,north + PT,south)

2 (1)

Static pressure was computed by the difference of total pressure from delta pressure. The

north and south probes were calculated separately.

PS,north = PT,north − ΔPnorth, PS,south = PT,south − ΔPsouth (2)

The static pressure of the bellmouth was then averaged using the static pressure readings

from the north and south bellmouth pitot-static probes, equation 3.

PS,bm = (PS,north + PS,south)

2 (3)

Facility total temperature, equation 4, was calculated based on the average of the 24

RTDs on the leading edge of the D-corner turning vanes.

TT,davg = 1

24



24

i=1

TT,d,i (4)

Utilizing the bellmouth total pressure and static pressure, Mach number at the bellmouth

is computed using equation 5.

Mbm =



2

γ − 1

⎡

⎣



PT,bm

PS,bm 	γ−1

γ

− 1

⎤

⎦ (5)

NASA/CR—2013-217812 13
Facility dynamic pressure, equation 6 is then calculated using bellmouth Mach number,

Mbm and bellmouth static pressure PS,bm.

qbm = γ

2

PS,bm · M2

bm (6)

9-foot Survey Rake Calculations

Data collected by the 9-ft survey rake are used to construct Mach number and static

pressure calibration curves. Additionally, the collected data are examined to check for flow

quality in the facility.

The average of the four static pressure taps on each of the 11 probes was used to calculate

the rake static pressure for each probe.

PS,rake = (P6 + P7 + P8 + P9)

4 (7)

Mach number was computed based on the rake total pressure to static pressure ratio.

Mrake =



2

γ − 1

⎡

⎣



PT,rake

PS,rake 	γ−1

γ

− 1

⎤

⎦ (8)

The correction equations or local values for total and static pressure are based on the

rake Mach number. Co and Cq are functions of Mrake and are experimentally determined

during calibration of the pressure probe flow-angle [4]. Local static and total pressure are

computed as shown.

PT,local = PT,rake − Co(Mrake) [PT,rake − PS,rake] (9)

PS,local = PT,local − (PT,rake − PS,rake)

Cq(Mrake) (10)

The local test section Mach number (equation 11) for each probe is determined using

PS,local and PT,local.

Mlocal =



2

γ − 1

⎡

⎣



PT,local

PS,local 	γ−1

γ

− 1

⎤

⎦ (11)

Local dynamic pressure in the test section is calculated per equation 12 below.

qlocal = γ

2

PS,local · M2

local (12)

NASA/CR—2013-217812 14
Flow Angularity

The following equations are used to calculate pitch and yaw flow-angle data from the

pressure data obtained from the 45 ◦ offset pressure ports on the front of the hemispherical

head probe. The average of these four 45 ◦ offset pressure ports is used to calculate Pavg,

equation 13.

Pavg = (P1 + P2 + P3 + P4)

4 (13)

The pressure coefficients Cα and Cβ are calculated for both pitch and yaw. The pitch

pressure coefficient, Cα, equation 14 is calculated using the 45 ◦ offset pressure ports in the

pitch plane, P1 and P3 and the difference between the total pressure in the center of the

hemispherical probe, P5, and the average of all four 45 ◦ offset pressure ports. Similarly, the

yaw pressure coefficient, Cβ, equation 15 is calculated using the 45 ◦ offset pressure ports in

the yaw plane, P2 and P4, and the difference between the total pressure in the center of the

hemispherical probe, P5, and the average of all four 45 ◦ offset pressure ports.

Cα = (P3 − P1)

(P5 − Pavg) (14)

Cβ = (P4 − P2)

(P5 − Pavg) (15)

Pitch angle, α, and yaw angle, β, are calculated using previously determined pitch and

yaw pressure coefficients and Mrake.

α = K0,α(Mrake) + K1,α(Mrake)Cα + Δα,arm + Δα,level (16)

β = K0,β(Mrake) + K2,β(Mrake)Cβ + Δβ,arm + Δβ,ruler (17)

The coefficients K0,α, K1,α, K0,β, and K2,β were experimentally determined [4]. The delta

coefficients are measurements made using a computer-aided inspection arm, an inclinometer,

and a ruler.

Turbulence Intensity

During this particular test entry one hot-wire and four hot film probes were used. The

hot-wire was positioned near the ceiling at 60-inches and the hot films were places in the

remaining four slots below the hot-wire. The hot-wire and film probes were calibrated in situ

in the IRT at the beginning of testing at each new position. In situ calibration data sweeps

were completed at velocities of 50, 90, 120, 150, and 170 knots and with the spraybar air

pressure at 0 psig. These in situ calibration data sweeps and a known velocity from a 5-hole

hemispherical head probed attached to the side of the rake were used to develop coefficients

A, B and n seen in King’s Law [7] below, (equation 18).

E2 = A + B · Qn or Q =



(E2 − A)

B


1/n

(18)

NASA/CR—2013-217812 15
Once the coefficients were developed, King’s Law was again used to calculate measured

velocity from the hot-wire/film voltages for each acquired data point. The variable Q is the

measured velocity, and since single wires or films were used, it is assumed that Q equals the

axial component only. Using the now calculated velocity values, a temporal mean velocity

and standard deviation for each steady state data point, acquired at a rate of 1kHz for 10

seconds, is calculated. Dividing the root mean square of the instantaneous velocity by the

mean velocity yields turbulence intensity.

2D RTD Array Calculations

Total temperature data recorded by the 2D RTD array requires a temperature recovery

correction, equation 19. Experiments to determine the recovery coefficients for the RTDs on

the 2D RTD array were performed in 2005 [5].

TT,local = (C0 + C1Mts + C2M2

ts)TT,array (19)

This local total temperature is then used to develop a calibration curve between the 2D

RTD array in the test section and the D-corner RTDs.

Discussion of Results

The following section will discuss the results of the 2012 IRT Aero-Thermal Calibration.

This section will begin by discussing a pressure discrepancy that was found during the course

of testing and how it was resolved. The aero-thermal calibration curves used for determining

the operating conditions in the IRT will be discussed. Flow quality results will be presented

with respect to flow quality goals for icing wind tunnels.

Pressure Discrepancy

No pressure data is being reported out for the January 2012, 300 knots test points.

The calibration team intended to recollect the data in May 2012 but was unable to, due to

schedule conflicts. The following is a description of why the 300 knots test points were not

used for this calibration. Therefore, the calibration curves presented in the next section are

only good to 250 knots.

During post processing of the data it was found that at the 300 knots test points, data

acquired by the 9-foot survey rake showed an unusual drop in static pressure. This drop

was seen only in the 300 knots case. The pressure data that had been collected with the

quick-check rake was then examined and the static pressure drop was seen again by this

second piece of hardware. Investigation ensued at the facility and it was found that the

reference pressure 90 degree elbow line, shown in Figure 13(a), was not properly connected.

This resulted in the balance chamber leakage flow to skew all ESP pressure readings low

whenever the IRT was operated at greater than 250 knots. The extra pipe length shown in

Figure 13(b) allows for the pressure to be read without an influence from outside sources

including a fan and other equipment in the room.

NASA/CR—2013-217812 16
Figure 13: (a)The pipe exiting the balance chamber of the IRT and the joint at which the

90 degree elbow was disconnected. (b)The 90 degree elbow as installed.

Aero-Thermal Calibration Curves

As mentioned, one of the primary goals of this calibration cycle was to update the

aero-thermal calibration curves used in the computing subroutine IRTAT which is used to

set conditions in the test section. Figure 14, Figure 15, and Figure 16 are the updated

calibration relationships for Mach number, static pressure, and total temperature. It can

been seen that the curves are linear in nature which is what is most desirable for calibration

relationships.

Figure 14: Mach number calibration for the IRT from the 2012 full aero-thermal calibration.

NASA/CR—2013-217812 17
Figure 15: Static pressure calibration for the IRT from the 2012 full aero-thermal calibration.

Figure 16: Total temperature calibration for the IRT from the 2012 full aero-thermal calibration.

NASA/CR—2013-217812 18
Flow Quality Goals

Table 5 is a summary of Aero-Thermal flow quality goals for an icing wind tunnel [1]. The

IRT flow quality with respect to the flow quality goals will be discussed in the subsequent

sections.

Table 5: Aero-thermal flow quality goals for an icing tunnel test section.

Parameter Measurement Test Tunnel

Uncertainty Section Centerline

Spatial Temporal

Uniformity Stability

Airspeed ±1% ±2% ±2%

Static air temperature, -30 through +5 ◦C ±0.5 ◦C ±1 ◦C ±0.5 ◦C

Static air temperature, below −30 ◦C ±2 ◦C ±2 ◦C ±2 ◦C

Flow Angularity ±0.25 ◦ ±2 ◦ N/A

Turbulence (Pair = 0psig) ±0.25% < 2% ±2%

Turbulence (Pair = 60psig) ±0.25% < 2% ±2%

Only test section spatial uniformity will be discussed for the 2012 data. Data was acquired

for 10 seconds then averaged, not the minimum required 30 seconds to determine temporal

stability, therefore temporal stability will not be discussed for the 2012 aero-thermal calibration. It is recommended that data be acquired in future calibrations to enable temporal

stability to be calculated. Measurement uncertainty will nt be discussed for the 2012 aerothermal calibration either. A measurement uncertainty analysis (MUA) effort is currently

under way for the facilities at GRC and a report will be written upon completion of this

work.

Flow quality data for Mach number, total pressure, static pressure, and total temperature

are presented in x-y plots to facilitate the viewing of as many features of the flow field as

possible. For easier visual comparison the surface plots of the temperature of the test section

is presented next to the surface plot of the temperature of D-corner.

Turbulence Intensity

Data shown in Figure 17 illustrates the turbulence intensity seen at the horizontal and

vertical centerline of the test section with a spraybar air pressure of 0 psig. Turbulence

intensity, u

/U, is shown plotted with respect to test section velocity, U(kts). Facility changes

that could affect turbulence intensity are summarized in the bottom right of Figure 17. The

standard deviations shown on the 2009 and 2012 data are from 4 time traces taken at the

same condition. The data is not available to develop standard deviations for data from 2005

and before. A full aero-thermal calibration was completed in 2006, but the data has not

been reduced to be added to Figure 17 at the time of this publication.

Results for turbulence intensity is shown in Figure 18. The turbulence intensity, u

/U,

is plotted with respect to the turn table centerline survey plane. A higher turbulence at

centerline is typically seen due to the spray bar center support. While the total number

NASA/CR—2013-217812 19
Figure 17: IRT Turbulence Intensity, Historical Comparison at horizontal and vertical centerline, Pair = 0psig.

of nozzles were reduced, 7 air-only atomizing nozzles located at the bottom center of the

spraybars were added to mix out the icing cloud, thereby increasing turbulence intensity. The

IRT will not have the low-turbulence levels of a wind tunnel used for aerodynamics testing.

This is a result of the lack of flow manipulators like screens and honeycomb straighteners

due to the icing conditions.

Table 6 illustrates the measured turbulence intensity with respect to test section spatial

uniformity. It can be seen that most test section spatial uniformity test points meet the

SAE flow quality goal of < 2%. The test points that do not meet the < 2% criteria is the

50 knots, 30 psi and 60 psi spray bar air pressure conditions.

Table 6: Turbulence Intensity Test Section Spatial Uniformity

0 psi 30 psi 60 psi

50 knots 0.844% 2.004% 2.784%

90 knots 0.905% 1.299% 1.659%

120 knots 1.231% 1.394% 1.567%

150 knots 1.188% 1.284% 1.411%

170 knots 1.173% 1.240% 1.33%

NASA/CR—2013-217812 20
Flow Angularity

Results for the test section flow angularity as measured by the 5-hole probes mounted

on the 9-ft survey rake is shown in Figure 19. The vectors shown in Figure 19 only reflect

the magnitude and direction of the local air flow, but not airspeed. For reference, +1◦ in

pitch and yaw is noted on each figure. The wall flow angularity behaviour has been seen in

previous data sets as far back as 2004. Most of the variation in the flow-angle orientation is

probably due to disturbances generated by the spraybars

Table 7 illustrates the flow angularity test section spatial uniformity for the test conditions

acquired. The 90 to 250 knots cases meet the SAE flow quality goals as laid out in Table 5.

The 50 knots test conditions does not meet the SAE flow quality goal of ±2 ◦. Tunnel

centerline spatial uniformity is not examined as part of the SAE flow quality goals for an

icing wind tunnel.

Table 7: Flow Angularity Test Section Spatial Uniformity

0 psi 30 psi 60 psi

50 knots ±2.562 ◦ ±2.464 ◦ ±2.433 ◦

90 knots ±0.919 ◦ ±0.877 ◦ ±0.781 ◦

120 knots ±0.648 ◦ ±0.472 ◦ ±0.531 ◦

150 knots ±0.594 ◦ ±0.538 ◦ ±0.465 ◦

170 knots ±0.622 ◦ ±0.581 ◦ ±0.578 ◦

200 knots ±0.654 ◦ ±0.583 ◦ ±0.578 ◦

250 knots ±0.626 ◦ ±0.785 ◦ ±0.645 ◦

Mach Number

Results for Mach number are shown in Figure 20. Mach number in the test section, Mts,

is normalized by Mach number at the bellmouth, Mbm, and plotted with respect to the width

of the test section in inches. The normalization of the test section to bellmouth for each

condition is done to remove run-to-run variations. Delta Mach number, each major division

on the vertical axis in Figure 20 helps to illustrate the absolute Mach number variation

seen in the data. Also, examining Figure 20, it is seen that the spraybar air injection has a

minimal affect on Mach number.

Table 8 illustrates the airspeed test section spatial uniformity. All of the acquired test

conditions meet the test section spatial uniformity flow quality goal of ±2%, as laid out in

Table 5.

Total Pressure

Results for total pressure are shown in Figure 21. Total pressure in the test section,

PT,ts, is normalized by total pressure at the bellmouth, PT,bm, and plotted with respect to

the width of the test section in inches. The normalization of the test section to bellmouth

for each condition is done to remove run-to-run variations. A delta total pressure is seen

NASA/CR—2013-217812 21
Table 8: Airspeed Test Section Spatial Uniformity

0 psi 30 psi 60 psi

50 knots ±0.846% ±1.476% ±0.922%

90 knots ±0.518% ±0.585% ±0.506%

120 knots ±0.623% ±0.513% ±0.564%

150 knots ±0.563% ±0.491% ±0.522%

170 knots ±0.483% ±0.518% ±0.522%

200 knots ±0.620% ±0.504% ±0.506%

250 knots ±0.553% ±0.581% ±0.517%

in the bottom right corner of the plots to help relate the ratios presented to the absolute

quantity of each y-axis division in Figure 21. Further examining Figure 21, it is seen that

the spraybar air injection does have an affect on the total pressure distribution in the test

section. The largest effects of the spray bars are seen at lower test section airspeeds and near

the test section boundaries. For example the effect of the spraybars is more pronounced at

the inner wall (0-24 inches) and the outer wall (84-108 inches). The flow in the core of the

test section is seen to be minimally affected.

Static Pressure

Results for static pressure is shown in Figure 22. Static pressure in the test section, PS,ts,

is normalized by static pressure at the bellmouth, PS,bm, and plotted with respect to the

width of the test section in inches. The normalization of the test section to bellmouth for

each condition is done to remove run-to-run variations. A delta static pressure is shown in

the bottom right corner of the plots to help relate the quantity of one tick in Figure 22 to the

ratio presented. Also, examining Figure 22 further, it is seen that the spraybar air injection

does not have a significant effect on the static pressure distribution in the test section.

Total Temperature

Results for total temperature is shown in Figure 23. Test section total temperature,

TT,ts,array,

◦C, is shown plotted with respect to the width of the test section in inches, Figure 23.

Table 9 lists the test section spatial uniformity for the test conditions that were acquired.

At a total temperature test point of −1◦C the test section temperature variation is approximately ±0.25◦C. However, at colder total temperature test points of −30◦C and below,

the test section variation is approximately ±0.5◦C to ±1.3◦C. This larger variation is seen

because the 80−85◦C spraybar air is more pronounced in the test section at the much colder

temperatures near the bottom of the IRT operating range. The last ten rows of Table 9 are

hysteresis test points. All of the data in Table 9 meets its respective criteria as laid out in

Table 5 when referenced to test section temperature.

NASA/CR—2013-217812 22
Table 9: Temperature Test Section Spatial Uniformity

0 psi 30 psi 60 psi

TT,davg = 7 ◦C, 200 knots ±0.299 ◦C N/A N/AC

TT,davg = 6 ◦C, 150 knots ±0.287 ◦C N/A N/A

TT,davg = 6 ◦C, 100 knots ±0.273 ◦C N/A N/A

TT,davg = 6 ◦C, 50 knots ±0.435 ◦C N/A N/A

TT,davg = 5 ◦C, 220 knots ±0.241 ◦C ±0.246 ◦C ±0.263 ◦C

TT,davg = 4 ◦C, 50 knots ±0.394 ◦C ±0.564 ◦C ±0.704 ◦C

TT,davg = 4 ◦C, 130 knots ±0.209 ◦C ±0.197 ◦C ±0.320 ◦C

TT,davg = 6 ◦C, 300 knots ±0.263 ◦C ±0.283 ◦C ±0.292 ◦C

TT,davg = 3 ◦C, 220 knots N/A ±0.243 ◦C N/A

TT,davg = 2 ◦C, 130 knots N/A ±0.340 ◦C N/A

TT,davg = 2 ◦C, 220 knots N/A ±0.264 ◦C N/A

TT,davg = 1 ◦C, 130 knots N/A ±0.311 ◦C N/A

TT,davg = 1 ◦C, 220 knots N/A ±0.257 ◦C N/A

TT,davg = 0 ◦C, 130 knots N/A ±0.197 ◦C N/A

TT,davg = 0 ◦C, 220 knots ±0.234 ◦C ±0.194 ◦C ±0.163 ◦C

TT,davg = −2 ◦C, 50 knots ±0.303 ◦C ±0.559 ◦C ±0.450 ◦C

TT,davg = −1 ◦C, 130 knots ±0.210 ◦C ±0.229 ◦C ±0.296 ◦C

TT,davg = 1 ◦C, 300 knots ±0.611 ◦C ±0.984 ◦C ±0.935 ◦C

TT,davg = −15 ◦C, 220 knots ±0.403 ◦C ±0.359 ◦C ±0.380 ◦C

TT,davg = −17 ◦C, 50 knots ±0.883 ◦C ±0.820 ◦C ±1.007 ◦C

TT,davg = −16 ◦C, 130 knots ±0.315 ◦C ±0.306 ◦C ±0.697 ◦C

TT,davg = −14 ◦C, 300 knots ±0.436 ◦C ±0.488 ◦C ±0.516 ◦C

TT,davg = −30 ◦C, 220 knots ±0.512 ◦C ±0.485 ◦C ±0.503 ◦C

TT,davg = −33 ◦C, 50 knots ±1.378 ◦C ±1.009 ◦C ±1.300 ◦C

TT,davg = −33 ◦C, 130 knots ±0.417 ◦C ±0.421 ◦C ±0.945 ◦C

TT,davg = −28 ◦C, 300 knots ±0.594 ◦C ±0.604 ◦C ±0.614 ◦C

TT,davg = −31 ◦C, 220 knots N/A ±0.312 ◦C N/A

TT,davg = −33 ◦C, 130 knots N/A ±0.800 ◦C N/A

TT,davg = −15 ◦C, 220 knots N/A ±0.566 ◦C N/A

TT,davg = −16 ◦C, 130 knots N/A ±0.397 ◦C N/A

TT,davg = −3 ◦C, 220 knots N/A ±0.373 ◦C N/A

TT,davg = −4 ◦C, 130 knots N/A ±0.859 ◦C N/A

TT,davg = −2 ◦C, 220 knots N/A ±0.339 ◦C N/A

TT,davg = −3 ◦C, 130 knots N/A ±0.372 ◦C N/A

TT,davg = −1 ◦C, 220 knots N/A ±0.311 ◦C N/A

TT,davg = −2 ◦C, 130 knots N/A ±0.311 ◦C N/A

Test section to D-corner comparison

Figure 24 allows for an easier visual comparison of the temperature distribution in the test

section with respect to the temperature distribution at D-corner at a test condition. This

NASA/CR—2013-217812 23
surface plot presentation was requested so customers have a better understanding of what

the temperature distribution in the test section looks like with respect to the temperature

distribution seen in D-corner. Figure 24 test section surface plots represent the difference

of the temperature of the individual RTD in the array from the average of the RTD array

temperature. Figure 24 D-corner surface plots represent the difference of the temperature

of the individual D-corner temperature measurement from the average of D-corner.

Study around 0◦C

An abridged study was conducted around 0◦C. Some airspeed data points were omitted in

the interest of time. D-corner total temperatures from 3◦C to −3◦C were considered for this

study. Test cases 130 knots and above were found to have an appearance of mixing in the

test section, with more of a temperature gradient behaviour seen in D-corner. The 50 knot

test cases showed temperature gradient behaviour in both the test section and D-corner. The

300 knots, D-corner total temperature of 1◦C case has the most pronounced case of mixing

in the test section. This case is seen in Figure 24 (ff, gg, and hh). It is believed that this

mixing behaviour is directly related the spraybar behaviour and therefore the icing cloud

behaviour in the test section around 0◦C.

Summary of Test Results

Aero-thermal calibration testing was completed in January and May 2012. Calibration testing was conducted to remap the test section flow quality and to re-develop the

aero-thermal calibration curves which relate the test section properties to the bellmouth

pitot-static probes and the D-corner RTD array. This testing occurred as a result of the

major modifications that occurred to the heat exchanger and the refrigeration plant. This

modification resulted in a lower achievable temperature in the test section. This is reflected

in the total temperature data that was presented in this report.

A pressure discrepancy was found at 300 knots and resolved. Overall, the IRT meets most

of the test section spatial uniformity flow quality goals set forth. There are a few specific test

points that do not meet the test section spatial uniformity criteria depicted in Table 5. The

tunnel centerline temporal stability will be examined as part of the next calibration. Also,

measurement uncertainty analysis will be presented in a separate paper upon completion of

the work that is currently in progress. At this time, an interim calibration is planned for

February 2013. When the interim calibration data is collected, it will be compared with full

calibration data set as validation.

Recommendations

The following recommendations were developed following the calibration entry. Their

implementation is suggested prior to the next calibration entry into the IRT.

• Acquire data for at least 30 seconds to enable the establishment of temporal stability

at tunnel centerline.

NASA/CR—2013-217812 24
• Include instrument uncertainties upon completion of the analysis.

• Update or replace the 9-foot rake hardware. If possible, develop a method to translate

the hardware to improve efficiency during the test entry.

NASA/CR—2013-217812 25
Figure 18: Test section turbulence intensity, as collected by the hot wire/film survey rake.

(a) Uts = 50 knots, Pair = 0 psig. (b) Uts = 50 knots, Pair = 30 psig. (c) Uts = 50 knots,

Pair = 60 psig.

Continued Figure 18: (d) Uts = 90 knots, Pair = 0 psig. (e) Uts = 90 knots, Pair = 30 psig.

(f) Uts = 90 knots, Pair = 60 psig.

NASA/CR—2013-217812 26
Continued Figure 18: (g) Uts = 120 knots, Pair = 0 psig. (h) Uts = 120 knots, Pair = 30

psig. (i) Uts = 120 knots, Pair = 60 psig.

Continued Figure 18: (j) Uts = 150 knots, Pair = 0 psig. (k) Uts = 150 knots, Pair = 30 psig.

(l) Uts = 150 knots, Pair = 60 psig.

NASA/CR—2013-217812 27
Continued Figure 18: (m) Uts = 170 knots, Pair = 0 psig. (n) Uts = 170 knots, Pair = 30

psig. (o) Uts = 170 knots, Pair = 60 psig.

NASA/CR—2013-217812 28
Figure 19: (a) Uts = 50 knots, Pair = 0 psig. (b) Uts = 90 knots, Pair = 0 psig. (c) Uts = 120 knots, Pair 

150 knots, Pair = 0 psig.

NASA/CR—2013-217812 29
Continued Figure 19: (e) Uts = 170 knots, Pair = 0 psig. (f) Uts = 200 knots, Pair = 0 psig. (g) Uts = 250 

NASA/CR—2013-217812 30
Continued Figure 19: (i) Uts = 50 knots, Pair = 30 psig. (j) Uts = 90 knots, Pair = 30 psig. (k) Uts = 120 k

(l) Uts = 150 knots, Pair = 30 psig.

NASA/CR—2013-217812 31
Continued Figure 19: (m) Uts = 170 knots, Pair = 30 psig. (n) Uts = 200 knots, Pair = 30 psig. (o) Uts = 

psig.

NASA/CR—2013-217812 32
Continued Figure 19: (q) Uts = 50 knots, Pair = 60 psig. (r) Uts = 90 knots, Pair = 60 psig. (s) Uts = 

psig. (t) Uts = 150 knots, Pair = 60 psig.

NASA/CR—2013-217812 33
Continued Figure 19: (u) Uts = 170 knots, Pair = 60 psig. (v) Uts = 200 knots, Pair = 60 psig. (w) Uts = 

psig.

NASA/CR—2013-217812 34
Figure 20: Mach number distribution data from the IRT test section. Data collected using the 9-ft sur

9 vertical positions over several tunnel runs. The test section Mach number data was normalized using number measurement. Approximate Mach number delta is indicated for each test section setting. (a)

Uts 

psig. (b)

Uts = 90 knots,

Pair = 0 psig. (c)

Uts = 120 knots,

Pair = 0 psig. (d)

Uts = 150 knots,

Pair = 0 

NASA/CR—2013-217812 35
Continued Figure 20: (e) Uts = 170 knots, Pair = 0 psig. (f) Uts = 200 knots, Pair = 0 psig. (g) Uts = 250 

NASA/CR—2013-217812 36
Continued Figure 20: (i) Uts = 50 knots, Pair = 30 psig. (j) Uts = 90 knots, Pair = 30 psig. (k) Uts = 

psig. (l) Uts = 150 knots, Pair = 30 psig.

NASA/CR—2013-217812 37
Continued Figure 20: (m) Uts = 170 knots, Pair = 30 psig. (n) Uts = 200 knots, Pair = 30 psig. (o) Uts 

30 psig.

NASA/CR—2013-217812 38
Continued Figure 20: (q) Uts = 50 knots, Pair = 60 psig. (r) Uts = 90 knots, Pair = 60 psig. (s) Uts = 

psig. (t) Uts = 150 knots, Pair = 60 psig.

NASA/CR—2013-217812 39
Continued Figure 20: (u) Uts = 170 knots, Pair = 60 psig. (v) Uts = 200 knots, Pair = 60 psig. (w) Uts = 

psig.

NASA/CR—2013-217812 40
Figure 21: Total pressure distribution data from the IRT test section. Data collected using the 9-ft surve

vertical positions over several tunnel runs. The test section total pressure data is normalized using the bellmeasurement. (a)

Uts = 50 knots,

Pair = 0 psig. (b)

Uts = 90 knots,

Pair = 0 psig. (c)

Uts = 120 knots,

P

= 150 knots,

Pair = 0 psig.

NASA/CR—2013-217812 41
Continued Figure 21: (e) Uts = 170 knots, Pair = 0 psig. (f) Uts = 200 knots, Pair = 0 psig. (g) Uts = 250 

NASA/CR—2013-217812 42
Continued Figure 21: (i) Uts = 50 knots, Pair = 30 psig. (j) Uts = 90 knots, Pair = 30 psig. (k) Uts = 

psig. (l) Uts = 150 knots, Pair = 30 psig.

NASA/CR—2013-217812 43
Continued Figure 21: (m) Uts = 170 knots, Pair = 30 psig. (n) Uts = 200 knots, Pair = 30 psig. (o) Uts 

30 psig.

NASA/CR—2013-217812 44
Continued Figure 21: (q) Uts = 50 knots, Pair = 60 psig. (r) Uts = 90 knots, Pair = 60 psig. (s) Uts = 

psig. (t) Uts = 150 knots, Pair = 60 psig.

NASA/CR—2013-217812 45
Continued Figure 21: (u) Uts = 170 knots, Pair = 60 psig. (v) Uts = 200 knots, Pair = 60 psig. (w) Uts = 

psig.

NASA/CR—2013-217812 46
Figure 22: Static pressure distribution data from the IRT test section. Data collected using the 9-ft surve

vertical positions over several tunnel runs. (a)

Uts = 50 knots,

Pair = 0 psig. (b)

Uts = 90 knots,

Pair = 

knots,

Pair = 0 psig. (d)

Uts = 150 knots,

Pair = 0 psig.

NASA/CR—2013-217812 47
Continued Figure 22: (e) Uts = 170 knots, Pair = 0 psig. (f) Uts = 200 knots, Pair = 0 psig. (g) Uts = 250 

NASA/CR—2013-217812 48
Continued Figure 22: (i) Uts = 50 knots, Pair = 30 psig. (j) Uts = 90 knots, Pair = 30 psig. (k) Uts = 

psig. (l) Uts = 150 knots, Pair = 30 psig.

NASA/CR—2013-217812 49
Continued Figure 22: (m) Uts = 170 knots, Pair = 30 psig. (n) Uts = 200 knots, Pair = 30 psig. (o) Uts 

30 psig.

NASA/CR—2013-217812 50
Continued Figure 22: (q) Uts = 50 knots, Pair = 60 psig. (r) Uts = 90 knots, Pair = 60 psig. (s) Uts = 

psig. (t) Uts = 150 knots, Pair = 60 psig.

NASA/CR—2013-217812 51
Continued Figure 22: (u) Uts = 170 knots, Pair = 60 psig. (v) Uts = 200 knots, Pair = 60 psig. (w) Uts = 

psig.

NASA/CR—2013-217812 52
Figure 23: Total Temperature test section temperature distribution, as collected by the 2D RTD survey 

knots,

TT,davg = 5.0◦C, Pair = 0 psig (b)

Uts = 217 knots,

TT,davg = 5.0◦C, Pair = 30 psig (c)

Uts = 217 kn

Pair = 60 psig

NASA/CR—2013-217812 53
Continued Figure 23: (d) Uts = 50 knots, TT,davg = 3.6◦C, Pair = 0 psig, (e) Uts = 50 knots, TT,davg = 3.6◦

Uts = 50 knots, TT,davg = 3.6◦C, Pair = 60 psig

NASA/CR—2013-217812 54
Continued Figure 23: (g) Uts = 130 knots, TT,davg = 3.9◦C, Pair = 0 psig (h) Uts = 130 knots, TT,davg = 3

(i) Uts = 130 knots, TT,davg = 3.9◦C, Pair = 60 psig

NASA/CR—2013-217812 55
Continued Figure 23: (j) Uts = 300 knots, TT,davg = 6.3◦C, Pair = 0 psig (k) Uts = 300 knots, TT,davg = 6

(l) Uts = 300 knots, TT,davg = 6.4◦C, Pair = 60 psig

NASA/CR—2013-217812 56
Continued Figure 23: (m) Uts = 220 knots, TT,davg = 3.0◦C, Pair = 30 psig (n) Uts = 130 knots, TT,davg = 

(o) Uts = 220 knots, TT,davg = 2.0◦C, Pair = 30 psig

NASA/CR—2013-217812 57
Continued Figure 23: (p) Uts = 130 knots, TT,davg = 1.0◦C, Pair = 30 psig (q) Uts = 220 knots, TT,davg = 

(r) Uts = 130 knots, TT,davg = 0.0◦C, Pair = 30 psig

NASA/CR—2013-217812 58
Continued Figure 23: (s) Uts = 220 knots, TT,davg = 0.0◦C, Pair = 0 psig (t) Uts = 220 knots, TT,davg = 0

(u) Uts = 220 knots, TT,davg = 0.0◦C, Pair = 60 psig

NASA/CR—2013-217812 59
Continued Figure 23: (v) Uts = 50 knots, TT,davg = -1.5◦C, Pair = 0 psig (w) Uts = 50 knots, TT,davg = -1

(x) Uts = 50 knots, TT,davg = -1.5◦C, Pair = 60 psig

NASA/CR—2013-217812 60
Continued Figure 23: (y) Uts = 130 knots, TT,davg = -1.1◦C, Pair = 0 psig (z) Uts = 130 knots, TT,davg = -

(aa) Uts = 130 knots, TT,davg = -1.1◦C, Pair = 60 psig

NASA/CR—2013-217812 61
Continued Figure 23: (bb) Uts = 220 knots, TT,davg = -15.1◦C, Pair = 0 psig (cc) Uts = 220 knots, TT,davg 

psig (dd) Uts = 220 knots, TT,davg = -15.1◦C, Pair = 60 psig

NASA/CR—2013-217812 62
Continued Figure 23: (ee) Uts = 50 knots, TT,davg = -16.9◦C, Pair = 0 psig (ff) Uts = 50 knots, TT,davg = -1

(gg) Uts = 50 knots, TT,davg = -16.9◦C, Pair = 60 psig

NASA/CR—2013-217812 63
Continued Figure 23: (hh) Uts = 130 knots, TT,davg = -16.4◦C, Pair = 0 psig (ii) Uts = 130 knots, TT,davg 

psig (jj) Uts = 130 knots, TT,davg = -16.4◦C, Pair = 60 psig

NASA/CR—2013-217812 64
Continued Figure 23: (kk) Uts = 300 knots, TT,davg = -13.6◦C, Pair = 0 psig (ll) Uts = 300 knots, TT,davg 

psig (mm) Uts = 300 knots, TT,davg = -13.6◦C, Pair = 60 psig

NASA/CR—2013-217812 65
Continued Figure 23: (nn) Uts = 220 knots, TT,davg = -30.0◦C, Pair = 0 psig (oo) Uts = 220 knots, TT,davg 

psig (pp) Uts = 220 knots, TT,davg = -30.0◦C, Pair = 60 psig

NASA/CR—2013-217812 66
Continued Figure 23: (qq) Uts = 50 knots, TT,davg = -33.3◦C, Pair = 0 psig (rr) Uts = 50 knots, TT,davg = 

psig (ss) Uts = 50 knots, TT,davg = -33.3◦C, Pair = 60 psig

NASA/CR—2013-217812 67
Continued Figure 23: (tt) Uts = 130 knots, TT,davg = -32.6◦C, Pair = 0 psig (uu) Uts = 130 knots, TT,davg 

psig (vv) Uts = 130 knots, TT,davg = -32.6◦C, Pair = 60 psig

NASA/CR—2013-217812 68
Continued Figure 23: (ww) Uts = 300 knots, TT,davg = -28.2◦C, Pair = 0 psig (xx) Uts = 300 knots, TT,da

30 psig (yy) Uts = 300 knots, TT,davg = -28.0◦C, Pair = 60 psig

NASA/CR—2013-217812 69
Continued Figure 23: (zz) Uts = 220 knots, TT,davg = -30.7◦C, Pair = 30 psi (aaa) Uts = 130 knots, TT,davg 

psig

NASA/CR—2013-217812 70
Continued Figure 23: (bbb) Uts = 220 knots, TT,davg = -14.9◦C, Pair = 30 psig (ccc) Uts = 130 knots, TT,d

30 psig

NASA/CR—2013-217812 71
Continued Figure 23: (ddd) Uts = 220 knots, TT,davg = -3.1◦C, Pair = 30 psig (eee) Uts = 130 knots, TT,d

30 psig

NASA/CR—2013-217812 72
Continued Figure 23: (fff) Uts = 220 knots, TT,davg = -1.8◦C, Pair = 30 psig (ggg) Uts = 130 knots, TT,davg 

psig

NASA/CR—2013-217812 73
Continued Figure 23: (hhh) Uts = 220 knots, TT,davg = -0.8◦C, Pair = 30 psig (iii) Uts = 130 knots, TT,davg 

psig

NASA/CR—2013-217812 74
Figure 24: Test section versus D-corner surface plots (a) Vknots = 200 knots, TT,davg = 7◦C,

Pair = 0 psig

Continued Figure 24: (b) Vknots = 150 knots, TT,davg = 6◦C, Pair = 0 psig

NASA/CR—2013-217812 75
Continued Figure 24: (c) Vknots = 100 knots, TT,davg = 6◦C, Pair = 0 psig

Continued Figure 24: (d) Vknots = 50 knots, TT,davg = 6◦C, Pair = 0 psig

NASA/CR—2013-217812 76
Continued Figure 24: (e) Vknots = 220 knots, TT,davg = 5◦C, Pair = 0 psig

Continued Figure 24: (f) Vknots = 220 knots, TT,davg = 5◦C, Pair = 60 psig

NASA/CR—2013-217812 77
Continued Figure 24: (g) Vknots = 220 knots, TT,davg = 5◦C, Pair = 30 psig

Continued Figure 24: (h) Vknots = 50 knots, TT,davg = 4◦C, Pair = 0 psig

NASA/CR—2013-217812 78
Continued Figure 24: (i) Vknots = 50 knots, TT,davg = 4◦C, Pair = 60 psig

Continued Figure 24: (j) Vknots = 50 knots, TT,davg = 4◦C, Pair = 30 psig

NASA/CR—2013-217812 79
Continued Figure 24: (k) Vknots = 130 knots, TT,davg = 4◦C, Pair = 0 psig

Continued Figure 24: (l) Vknots = 130 knots, TT,davg = 4◦C, Pair = 60 psig

NASA/CR—2013-217812 80
Continued Figure 24: (m) Vknots = 130 knots, TT,davg = 4◦C, Pair = 30 psig

Continued Figure 24: (n) Vknots = 300 knots, TT,davg = 6◦C, Pair = 0 psig

NASA/CR—2013-217812 81
Continued Figure 24: (o) Vknots = 300 knots, TT,davg = 6◦C, Pair = 60 psig

Continued Figure 24: (p) Vknots = 300 knots, TT,davg = 6◦C, Pair = 30 psig

NASA/CR—2013-217812 82
Continued Figure 24: (q) Vknots = 220 knots, TT,davg = 3◦C, Pair = 30 psig

Continued Figure 24: (r) Vknots = 130 knots, TT,davg = 2◦C, Pair = 30 psig

NASA/CR—2013-217812 83
Continued Figure 24: (s) Vknots = 220 knots, TT,davg = 2◦C, Pair = 30 psig

Continued Figure 24: (t) Vknots = 130 knots, TT,davg = 1◦C, Pair = 30 psig

NASA/CR—2013-217812 84
Continued Figure 24: (u) Vknots = 220 knots, TT,davg = 1◦C, Pair = 30 psig

Continued Figure 24: (v) Vknots = 130 knots, TT,davg = 0◦C, Pair = 30 psig

NASA/CR—2013-217812 85
Continued Figure 24: (w) Vknots = 220 knots, TT,davg = 0◦C, Pair = 0 psig

Continued Figure 24: (x) Vknots = 220 knots, TT,davg = 0◦C, Pair = 60 psig

NASA/CR—2013-217812 86
Continued Figure 24: (y) Vknots = 220 knots, TT,davg = 0◦C, Pair = 30 psig

Continued Figure 24: (z) Vknots = 50 knots, TT,davg = -2◦C, Pair = 0 psig

NASA/CR—2013-217812 87
Continued Figure 24: (aa) Vknots = 50 knots, TT,davg = -2◦C, Pair = 60 psig

Continued Figure 24: (bb) Vknots = 50 knots, TT,davg = -2◦C, Pair = 30 psig

NASA/CR—2013-217812 88
Continued Figure 24: (cc) Vknots = 130 knots, TT,davg = -1◦C, Pair = 0 psig

Continued Figure 24: (dd) Vknots = 130 knots, TT,davg = -1◦C, Pair = 60 psig

NASA/CR—2013-217812 89
Continued Figure 24: (ee) Vknots = 130 knots, TT,davg = -1◦C, Pair = 30 psig

Continued Figure 24: (ff) Vknots = 300 knots, TT,davg = 1◦C, Pair = 0 psig

NASA/CR—2013-217812 90
Continued Figure 24: (gg) Vknots = 300 knots, TT,davg = 1◦C, Pair = 60 psig

Continued Figure 24: (hh) Vknots = 300 knots, TT,davg = 1◦C, Pair = 30 psig

NASA/CR—2013-217812 91
Continued Figure 24: (ii) Vknots = 220 knots, TT,davg = -15◦C, Pair = 0 psig

Continued Figure 24: (jj) Vknots = 220 knots, TT,davg = -15◦C, Pair = 60 psig

NASA/CR—2013-217812 92
Continued Figure 24: (kk) Vknots = 220 knots, TT,davg = -15◦C, Pair = 30 psig

Continued Figure 24: (ll) Vknots = 50 knots, TT,davg = -17◦C, Pair = 0 psig

NASA/CR—2013-217812 93
Continued Figure 24: (mm) Vknots = 50 knots, TT,davg = -17◦C, Pair = 60 psig

Continued Figure 24: (nn) Vknots = 50 knots, TT,davg = -17◦C, Pair = 30 psig

NASA/CR—2013-217812 94
Continued Figure 24: (oo) Vknots = 130 knots, TT,davg = -16◦C, Pair = 0 psig

Continued Figure 24: (pp) Vknots = 130 knots, TT,davg = -16◦C, Pair = 60 psig

NASA/CR—2013-217812 95
Continued Figure 24: (qq) Vknots = 130 knots, TT,davg = -16◦C, Pair = 30 psig

Continued Figure 24: (rr) Vknots = 300 knots, TT,davg = -14◦C, Pair = 0 psig

NASA/CR—2013-217812 96
Continued Figure 24: (ss) Vknots = 300 knots, TT,davg = -14◦C, Pair = 60 psig

Continued Figure 24: (tt) Vknots = 300 knots, TT,davg = -14◦C, Pair = 30 psig

NASA/CR—2013-217812 97
Continued Figure 24: (uu) Vknots = 220 knots, TT,davg = -30◦C, Pair = 0 psig

NASA/CR—2013-217812 98
Continued Figure 24: (vv) Vknots = 220 knots, TT,davg = -30◦C, Pair = 60 psig

Continued Figure 24: (ww) Vknots = 220 knots, TT,davg = -30◦C, Pair = 30 psig

NASA/CR—2013-217812 99
Continued Figure 24: (xx) Vknots = 50 knots, TT,davg = -33◦C, Pair = 0 psig

Continued Figure 24: (yy) Vknots = 50 knots, TT,davg = -33◦C, Pair = 60 psig

NASA/CR—2013-217812 100
Continued Figure 24: (zz) Vknots = 50 knots, TT,davg = -33◦C, Pair = 30 psig

Continued Figure 24: (aaa) Vknots = 130 knots, TT,davg = -33◦C, Pair = 0 psig

NASA/CR—2013-217812 101
Continued Figure 24: (bbb) Vknots = 130 knots, TT,davg = -33◦C, Pair = 60 psig

Continued Figure 24: (ccc) Vknots = 130 knots, TT,davg = -33◦C, Pair = 30 psig

NASA/CR—2013-217812 102
Continued Figure 24: (ddd) Vknots = 300 knots, TT,davg = -28◦C, Pair = 0 psig

Continued Figure 24: (eee) Vknots = 300 knots, TT,davg = -28◦C, Pair = 60 psig

NASA/CR—2013-217812 103
Continued Figure 24: (fff) Vknots = 300 knots, TT,davg = -28◦C, Pair = 30 psig

Continued Figure 24: (ggg) Vknots = 220 knots, TT,davg = -31◦C, Pair = 30 psig

NASA/CR—2013-217812 104
Continued Figure 24: (hhh) Vknots = 130 knots, TT,davg = -33◦C, Pair = 30 psig

Continued Figure 24: (iii) Vknots = 220 knots, TT,davg = -15◦C, Pair = 30 psig

NASA/CR—2013-217812 105
Continued Figure 24: (jjj) Vknots = 130 knots, TT,davg = -16◦C, Pair = 30 psig

Continued Figure 24: (kkk) Vknots = 220 knots, TT,davg = -3◦C, Pair = 30 psig

NASA/CR—2013-217812 106
Continued Figure 24: (lll) Vknots = 130 knots, TT,davg = -4◦C, Pair = 30 psig

Continued Figure 24: (mmm) Vknots = 220 knots, TT,davg = -2◦C, Pair = 30 psig

NASA/CR—2013-217812 107
Continued Figure 24: (nnn) Vknots = 130 knots, TT,davg = -3◦C, Pair = 30 psig

Continued Figure 24: (ooo) Vknots = 220 knots, TT,davg = -1◦C, Pair = 30 psig

NASA/CR—2013-217812 108
Continued Figure 24: (ppp) Vknots = 130 knots, TT,davg = -2◦C, Pair = 30 psig

NASA/CR—2013-217812 109
References

1. SAE Standards ARP(Aerospace Recommended Practice)5905, Calibration and Acceptance of Icing Wind Tunnels, 2003.

2. “Recommended Practice: Calibration of Subsonic and Transonic Wind Tunnels,” 2003.

3. Soeder, R.H., S. D. I. R. S. D. and Andracchio, C., “NASA Glenn Icing Research Tunnel

User Manual,” Tech. Rep. NASA/TM-2003-212004, 2003.

4. Gonsalez, J. and Arrington, E., “Five-Hole Flow Angle Probe Calibration for the NASA

Glenn Icing Research Tunnel,” Tech. rep., 2001.

5. Gonsalez, J. and Arrington, E., “Improvements to the Total Temperature Calibration

of the NASA Glenn Icing Research Tunnel,” Tech. Rep. NASA/CR-2005-213875, AIAA2005-4276, 2005.

6. Staff, A. R., “Equations, Tables, and Charts for Compressible Flow,” Tech. Rep. Report

1135, 1953, National Advisory Committee for Aeronautics.

7. Springer Handbook of Experimental Fluid Mechanics, Springer, 2007.

NASA/CR—2013-217812 110

REPORT DOCUMENTATION PAGE Form Approved 

OMB No. 0704-0188 

The 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 Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. 

Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB 

control number. 

PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. 

1. REPORT DATE (DD-MM-YYYY)

01-03-2013 

2. REPORT TYPE

Final Contractor Report 

3. DATES COVERED (From - To)

4. TITLE AND SUBTITLE

Aero-Thermal Calibration of the NASA Glenn Icing Research Tunnel (2012 Tests) 

5a. CONTRACT NUMBER

NNC05CA95C 

5b. GRANT NUMBER

5c. PROGRAM ELEMENT NUMBER

6. AUTHOR(S)

Pastor-Barsi, Christine; Arrington, E., Allen 

5d. PROJECT NUMBER

5e. TASK NUMBER

5f. WORK UNIT NUMBER

WBS 122711.03.07.03.02 

7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)

Sierra-Lobo, Inc. 

8. PERFORMING ORGANIZATION

 REPORT NUMBER

E-18548 

9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)

National Aeronautics and Space Administration 

Washington, DC 20546-0001 

10. SPONSORING/MONITOR'S

 ACRONYM(S)

NASA 

11. SPONSORING/MONITORING

 REPORT NUMBER

NASA/CR-2013-217812 

12. DISTRIBUTION/AVAILABILITY STATEMENT

Unclassified-Unlimited 

Subject Category: 09 

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

This publication is available from the NASA Center for AeroSpace Information, 443-757-5802

13. SUPPLEMENTARY NOTES

14. ABSTRACT

A full aero-thermal calibration of the NASA Glenn Icing Research Tunnel (IRT) was completed in 2012 following the major modifications 

to the facility that included replacement of the refrigeration plant and heat exchanger. The calibration test provided data used to fully 

document the aero-thermal flow quality in the IRT test section and to construct calibration curves for the operation of the IRT. 

15. SUBJECT TERMS

Wind tunnel calibration 

16. SECURITY CLASSIFICATION OF: 17. LIMITATION OF

 ABSTRACT

UU 

18. NUMBER

 OF 

 PAGES

126 

19a. NAME OF RESPONSIBLE PERSON

STI Help Desk (email:help@sti.nasa.gov) 

a. REPORT

U 

b. ABSTRACT

U 

c. THIS 

PAGE

U 

19b. TELEPHONE NUMBER (include area code)

443-757-5802 

Standard Form 298 (Rev. 8-98)

Prescribed by ANSI Std. Z39-18