Bruce L. Morin

Pratt & Whitney, East Hartford, Connecticut

Broadband Fan Noise Prediction System for 

Turbofan Engines

Volume 3: Validation and Test Cases

NASA/CR—2010-216898/VOL3

November 2010
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 via the Internet to help@

sti.nasa.gov

• Fax your question to the NASA STI Help Desk 

at 443–757–5803

• Telephone the NASA STI Help Desk at

 443–757–5802

• Write to:

 NASA Center for AeroSpace Information (CASI)

 7115 Standard Drive

 Hanover, MD 21076–1320
Bruce L. Morin

Pratt & Whitney, East Hartford, Connecticut

Broadband Fan Noise Prediction System for 

Turbofan Engines

Volume 3: Validation and Test Cases

NASA/CR—2010-216898/VOL3

November 2010

National Aeronautics and

Space Administration

Glenn Research Center

Cleveland, Ohio 44135

Prepared under Contract NAS3–27727
Acknowledgments

This work was performed under Contract NAS3-27727 (AST Task 13) from the NASA Glenn Research Center (GRC) with Dennis 

Huff as contract monitor. The author greatly appreciates the following contributions: Dennis Huff (GRC) and Edmane Envia (GRC) 

for overall direction and coordination the AST Noise Program; Donald Hanson (P&W, retired) and Stewart Glegg (Florida Atlantic 

University) for providing the noise prediction routines used in BFaNS; Ramons Reba (United Technologies Research Center) for 

his work on the cascade-response subroutines; Gary Podboy (GRC), Richard Woodward (GRC) and Christopher Hughes (GRC) 

for providing noise, performance and fl ow-fi eld data from the Pratt & Whitney and General Electric 22 in. diameter fan rigs that 

were tested at GRC; Ulrich Ganz (Boeing), John Premo (Boeing) and Timothy Patten (Boeing) for providing noise, performance 

and fl ow-fi eld data from the Boeing 18 in. diameter fan rig that was tested at Boeing; Tony Hoang (United Technologies Research 

Center) for his assistance with computer programming and running test cases; Jon Gilson (P&W), Aaron Farbo (P&W Intern) 

and Gary Willett (P&W retired) for their assistance with data reduction and analysis; Clint Ingram (formerly P&W) and Mark 

Stephens (P&W) for providing CFD predictions for the Pratt & Whitney 22 in. diameter fan rig; Wesley Lord (P&W), Douglas 

Mathews (P&W) and David Topol (P&W) for their helpful comments and suggestions regarding this work.

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://gltrs.grc.nasa.gov

This work was sponsored by the Fundamental Aeronautics Program 

at the NASA Glenn Research Center.

Level of Review: This material has been technically reviewed by expert reviewer(s).
NASA/CR—2010-216898/VOL3 iii

Summary

Pratt & Whitney has developed a Broadband Fan Noise Prediction System (BFaNS) for turbofan 

engines. This system computes the noise generated by turbulence impinging on the leading edges of the 

fan and fan exit guide vane, and noise generated by boundary-layer turbulence passing over the fan 

trailing edge. BFaNS has been validated on three fan rigs that were tested during the NASA Advanced 

Subsonic Technology Program (AST). The predicted noise spectra agreed well with measured data. The 

predicted effects of fan speed, vane count, and vane sweep also agreed well with measurements.

The noise prediction system consists of two computer programs: Setup_BFaNS and BFaNS.

Setup_BFaNS converts user-specified geometry and flow-field information into a BFaNS input file. From 

this input file, BFaNS computes the inlet and aft broadband sound power spectra generated by the fan and 

FEGV. The output file from BFaNS contains the inlet, aft and total sound power spectra from each noise 

source.

This report is the third volume of a three-volume set documenting the Broadband Fan Noise 

Prediction System:

Volume 1: Setup_BFaNS User’s Manual and Developer’s Guide

Volume 2: BFaNS User’s Manual and Developer’s Guide

Volume 3: Validation and Test Cases

The present volume begins with an overview of the Broadband Fan Noise Prediction System, 

followed by validation studies that were done on three fan rigs. It concludes with recommended 

improvements and additional studies for BFaNS. 

NASA/CR—2010-216898/VOL3 v

Contents

Summary......................................................................................................................................................iii

1.0 Introduction ..........................................................................................................................................1

2.0 Pratt & Whitney 22-in. Diameter Fan ..................................................................................................1

2.1 Acoustic Configuration...............................................................................................................1

2.2 Flow-Field Measurement Configuration.....................................................................................2

2.3 Approach Power..........................................................................................................................3

2.4 Effect of Fan Speed.....................................................................................................................3

3.0 General Electric 22-in. Diameter Fan...................................................................................................5

3.1 Acoustic Configurations .............................................................................................................6

3.2 Flow-Field Measurement Configuration.....................................................................................6

3.3 Approach Power, 54 Radial Vanes.............................................................................................7

3.4 Effect of Vane Configuration......................................................................................................8

4.0 Boeing 18-in. Diameter Fan ...............................................................................................................10

4.1 Acoustic Configurations ...........................................................................................................10

4.2 Flow-Field Measurement Configuration...................................................................................10

4.3 55 Percent Design Speed, Low Loading, Small Clearance.......................................................11

4.4 Effect of Fan Speed, Low Loading, Small Clearance...............................................................11

5.0 Concluding Remarks..........................................................................................................................12

6.0 Recommendations..............................................................................................................................13

Appendix A.—Pratt & Whitney/NASA Fan Rig Information....................................................................15

A.1 Fan No. 1, Flow-Path Geometry File........................................................................................15

A.2 Fan No. 1, Blade Geometry File..............................................................................................16

A.3 Fan No. 1, Vane Geometry File ................................................................................................17

Appendix B.—General Electric/NASA Fan Rig Information ....................................................................25

B.1 R4 Fan, 54 Radial Vanes, Flow-Path Geometry File................................................................26

B.1.1 R4 Fan, 54 Radial Vanes, Blade Geometry File........................................................ 28

B.1.2 R4 Fan, 54 Radial Vanes, Vane Geometry File .......................................................... 29

B.2 R4 Fan, 26 Radial Vanes, Flow-Path Geometry File................................................................31

B.2.3 R4 Fan, 26 Radial Vanes, Blade Geometry File ......................................................... 33

B.2.4 R4 Fan, 26 Radial Vanes, Vane Geometry File .......................................................... 34

B.3 R4 Fan, 26 Swept Vanes, Flow-Path Geometry File ................................................................36

B.3.5 B-4b. R4 Fan, 26 Swept Vanes, Blade Geometry File................................................ 38

B.3.6 R4 Fan, 26 Swept Vanes, Vane Geometry File........................................................... 39

Appendix C.—Boeing Fan Rig Information...............................................................................................53

C.1 Geometry Files..........................................................................................................................53

C.1.1 Boeing Rig, Flow-Path Geometry File........................................................................ 53

C.1.2 Boeing Rig, Blade Geometry File.............................................................................. 54

C.1.3 Boeing Rig, Vane Geometry File................................................................................ 54

Appendix D.—Turbulence Spectra, GE R4 and M5 Fans..........................................................................57

Appendix E.—Turbulence Spectra, P&W Fan Numbers 1 and 2...............................................................73

References...................................................................................................................................................85

List of Figures

Figure 1.—Fan broadband noise sources predicted by BFaNS. ...................................................................2

Figure 2.—Acoustic configuration, P&W fan. .............................................................................................2

Figure 3.—Flow-field measurement configuration, P&W fan. ....................................................................3

Figure 4.—Sound power spectra, approach power, P&W fan no. 1. (a) Calculations excluding 

blade noise. (b) Calculations including blade noise..............................................................................4
NASA/CR—2010-216898/VOL3 vi

Figure 5.—Effect of fan speed, P&W fan no. 1. (a) Calculations excluding blade noise. (b) 

Calculations including blade noise. ......................................................................................................5

Figure 6.—Acoustic configurations, GE fan: (a) 54 radial vanes (baseline); (b) 26 radial vanes; 

(c) 26 swept vanes; and (d) rotor alone.................................................................................................6

Figure 7.—Flow-field measurement configuration, GE fan. ........................................................................7

Figure 8.—Sound power spectrum, GE R4 fan, 54 radial vanes (approach power).....................................8

Figure 9.—Sound power spectrum, GE R4 fan, rotor alone (approach power)............................................8

Figure 10.—Effect of vane configuration: (a) Experimental data; (b) Calculations excluding 

blade noise; and (c) Calculations including blade noise.......................................................................9

Figure 11.—Acoustic configuration, Boeing fan........................................................................................10

Figure 12.—Flow field measurement configuration, Boeing fan. ..............................................................11

Figure 13.—Sound power spectrum, Boeing fan, 55 percent design speed (low loading, small 

clearance)............................................................................................................................................11

Figure 14.—Effect of fan speed, Boeing fan (low loading, small clearance): (a) Including blade 

noise; and (b) Excluding blade noise..................................................................................................12

Figure A.1—Fan no. 1 rig schematics. .......................................................................................................15

Figure A.2.—Fan no. 1, average velocity, station A...................................................................................19

Figure A.3.—Fan no. 1, average velocity, station B...................................................................................20

Figure A.4.—Fan no. 1, average turbulence intensity, station A................................................................21

Figure A.5.—Fan no. 1, average turbulence intensity, station B................................................................22

Figure A.6.—Fan no. 1, average turbulence scale, station A......................................................................23

Figure A.7.—Fan no. 1, average turbulence scale, station B......................................................................23

Figure B.1.—R4 fan rig schematics............................................................................................................25

Figure B.2.—R4 fan, average velocity, station A.......................................................................................42

Figure B.3.—R4 fan, average velocity, station B. ......................................................................................43

Figure B.4.—R4 fan, average turbulence intensity, station A. ...................................................................44

Figure B.5.—R4 fan, average turbulence intensity, station B. ...................................................................45

Figure B.6.—R4 fan, average turbulence scale, station A..........................................................................46

Figure B.7.—R4 fan, average turbulence scale, station B. .........................................................................46

Figure B.8.—M5 fan, average velocity, station A. .....................................................................................47

Figure B.9.—M5 fan, average velocity, station B. .....................................................................................48

Figure B.10.—M5 fan, average turbulence intensity, station A. ................................................................49

Figure B.11.—R4 fan, average turbulence intensity, station B. .................................................................50

Figure B.12.—M5 fan, average turbulence scale, station A. ......................................................................51

Figure B.13.—M5 fan, average turbulence scale, station B. ......................................................................51

Figure C.1.—Boeing fan rig schematics.....................................................................................................53

Figure D.1.—Source diagnostic test, R4 fan, approach, station A. ............................................................57

Figure D.2.—Source diagnostic test, R4 fan, approach, station B..............................................................61

Figure D.3.—Source diagnostic test, M5 fan, approach, station A.............................................................65

Figure D.4.—Source diagnostic test, M5 fan, approach, station B.............................................................69

Figure E.1.—P&W fan number 1 test, approach, station A........................................................................73

Figure E.2.—P&W fan number 1 test, approach, station B........................................................................75

Figure E.3.—P&W fan number 1 test, cutback, station B. .........................................................................77

Figure E.4.—P&W fan number 1 test, sideline, station A..........................................................................79

Figure E.5.—P&W fan number 1 test, sideline, station B. .........................................................................81

Figure E.6.—P&W fan number 2 test, sideline, station A..........................................................................83

List of Tables

Table 1.—Hot-Wire and LDV Data Used in Present Study, P&W Fan .......................................................2

Table 2.—Hot-Wire and LDV Data Used in Present Study, GE Fan ...........................................................7

Table 3.—Hot-Wire Data Used in Present Study, Boeing Fan...................................................................10
NASA/CR—2010-216898/VOL3 1

Broadband Fan Noise Prediction System for Turbofan Engines

Volume 3: Validation and Test Cases

Bruce L. Morin

Pratt & Whitney

East Hartford, Connecticut 06108

1.0 Introduction

In early turbofan engines, the fan blade passage tone and higher harmonics dominated the fan noise 

level when compared to fan broadband noise. However, engine makers have been very successful at 

reducing fan tone noise by decreasing fan tip speed, providing ample spacing between airfoil rows, 

carefully selecting the airfoil counts, and acoustically treating the fan duct. In fact, tone noise reduction 

has been so great that fan broadband noise is now a major contributor to the overall engine noise level.

Under NASA funding, Pratt & Whitney has developed a Broadband Fan Noise Prediction System 

(BFaNS) for turbofan engines. This prediction system is built around acoustic theories developed by 

Hanson (Refs. 1 to 4) and Glegg (Refs. 5 to 7). These theories account for noise generated by turbulence 

impinging on the leading edges of the fan and fan exit guide vane (FEGV), and noise generated by 

boundary-layer turbulence passing over the fan trailing edge. Figure 1 shows the fan broadband noise 

sources that can be predicted with BFaNS.

This report documents the validation studies that were performed on the following three fan rigs:

• Pratt & Whitney 22 in. diameter fan tested in the NASA Glenn Research Center 9- by 15-ft Low 

Speed Wind Tunnel

• General Electric 22 in. diameter fan tested in the NASA Glenn Research Center 9- by 15-ft Low 

Speed Wind Tunnel

• Boeing 18 in. diameter fan tested at Boeing Low Speed Aeroacoustic Facility (LSAF)

Volume 1 of this report series provides instructions for running Setup_BFaNS, and Volume 2 

provides instructions for running BFaNS.

2.0 Pratt & Whitney 22-in. Diameter Fan

This section describes the validation of BFANS using data acquired from a P&W 22-in. fan 

(designated Fan no. 1) that was tested in the 9- by 15-ft Low Speed Wind Tunnel at NASA Glenn 

Research Center. The experimental data consisted of farfield noise, Laser Doppler Velocimeter (LDV) 

and hot-wire (HW) measurements of the mean velocity and turbulence near the stator leading edge, and 

total-pressure and total-temperature profiles downstream from the fan.

The flow-field measurements were used in conjunction with CFD calculations to provide the input 

needed to run BFaNS. The BFaNS validation was done at three speeds corresponding to approach, 

cutback, and sideline power. The BFANS calculations were compared to experimental data in terms of 

total sound power spectra.

2.1 Acoustic Configuration

Figure 2 shows the fan configuration that was used during the acoustic tests. The rotor had a diameter 

of 22 in. and consisted of 18 blades. The stator configuration consisted of 45 radial vanes. Reference 8

provides a more detailed description of the acoustic setup and measurements. Appendix A provides a 

detailed description of the flow path, blade and vane geometry.
NASA/CR—2010-216898/VOL3 2

Figure 1.—Fan broadband noise sources predicted by BFaNS.

Figure 2.—Acoustic configuration, P&W fan.

2.2 Flow-Field Measurement Configuration

To facilitate the LDV and hot-wire measurements, the stator was moved 2.33 in. downstream from its 

nominal location as shown in Figure 3. This modification permitted velocity measurements to be obtained 

2.65 and 6.67 in. downstream from the fan tip trailing edge (Stations A and B, respectively). Note that 

Station A is upstream and Station B is downstream from the nominal location of the stator leading edge in 

the acoustic configuration (approximately 5.10 in. downstream from the rotor). Though not shown, a 

bellmouth inlet was installed during all LDV and hot-wire tests. Table 1 lists the LDV and HW data that 

were used in the present study (shaded cells indicate conditions where data was not acquired).

Appendix A shows plots of the mean and turbulent flow-field measurements acquired at Stations A 

and B. References 9 and 10 provide additional information on the flow-field data, along with preliminary 

BFaNS predictions.

TABLE 1.—HOT-WIRE AND LDV DATA USED IN PRESENT STUDY, P&W FAN

Corrected fan speed 

(rpm)

Acoustic 

condition

HW data at 

station A

HW Data at 

station B

LDV data at 

station A

LDV data at 

station B

5425 Approach Yes Yes Yes Yes

7525 Cutback ---- Yes No Yes

8750 Sideline Yes Yes Yes Yes

Simulated Core Flow

Centerline

B

L

A

D

E

V

A

N

E

B = 18

V = 45

Simulated Core Flow

Centerline

B

L

A

D

E

V

A

N

E

Simulated Core Flow

Centerline

B

L

A

D

E

V

A

N

E

B = 18

V = 45
NASA/CR—2010-216898/VOL3 3

Figure 3.—Flow-field measurement configuration, P&W fan.

2.3 Approach Power

Figure 4 shows calculated and measured sound power spectra at approach power. The calculations 

and measurements have been scaled to an 81-in. diameter fan. The calculations were done using LDV and 

HW data acquired at Stations A and B (hence, there are four calculated spectra). Recall that Station A is 

upstream from the vane leading edge, and Station B is downstream from the vane leading edge (see

Figure 2 and Figure 3). The calculations in Figure 4(a) exclude blade noise, while those in Figure 4(b)

include blade noise.

The calculated spectra in Figure 4(a) show good agreement with the measured data. Across most of 

the frequency range, the measured spectrum falls between the upper and lower limits of the calculated 

spectra. However, when blade noise is included (Figure 4(b)), the calculated spectra exceed the measured 

spectrum over most of the frequency range. These results suggest that BFaNS over-predicts the 

contribution of blade noise (mainly self noise) relative to vane noise.

Figure 4 also shows that the noise calculations based on HW data are approximately 3 dB greater than 

those based on LDV data. This result is consistent with the velocity profiles in Appendix A, which show 

that the HW measured a larger mean velocity than the LDV. Ideally, these two techniques should measure 

the same profile since the operating conditions were nominally the same between the two tests. Based on 

correspondence with NASA personnel (Ref. 11), the LDV data is believed to be the most accurate, and 

the hot-wire data should only be used to determine the turbulent length scale.

2.4 Effect of Fan Speed

Figure 5 shows calculated and measured sound power spectra at approach, cutback and sideline 

power. The calculations and measurements have been scaled to an 81-in. diameter fan. The calculations 

are based on the average of the calculations made with the LDV data at Stations A and B (the HW data 

was used to determine length scale only). The calculations in Figure 5(a) exclude blade noise, while those 

in Figure 5(b) include blade noise.

In general, the calculated spectra in Figure 5(a) show good agreement with the measured data, in 

terms of both level and shape. However, the calculated spectra do not exhibit the subtle “double-hump”

that is observed in the measured spectra. In Section 3.0, it will be shown that this “double hump”

indicates two separate noise sources; the first hump is associated with vane noise, and the second hump is 

associated with blade noise. When blade noise is included in the calculations (Figure 5(a)), the calculated 

spectra are significantly greater than the measured spectra, especially at the high-frequency end of the 

spectra. Again, this suggests that BFaNS over-predicts the contribution of blade noise relative to vane 

noise.

Simulated Core Flow

Centerline

A B

B

L

A

D

E

V

A

N

E

B = 18

V = 45

Simulated Core Flow

Centerline

A B

B

L

A

D

E

V

A

N

E

Simulated Core Flow

Centerline

A B

B

L

A

D

E

V

A

N

E

B = 18

V = 45
NASA/CR—2010-216898/VOL3 4

(a)

(b)

Figure 4.—Sound power spectra, approach power, P&W fan no. 1. (a) Calculations 

excluding blade noise. (b) Calculations including blade noise.

 

100

105

110

115

120

125

130

135

140

506380

100125160200250315400500630800

1000125016002000250031504000500063008000

10000

Frequency (Hz)

PWL (dB)

Computed Based On HW @ Sta. A

Computed Based On HW @ Sta. B

Computed Based On LDV @ Sta. A

Computed Based On LDV @ Sta. B

Measured

 

100

105

110

115

120

125

130

135

140

506380

100125160200250315400500630800

1000125016002000250031504000500063008000

10000

Frequency (Hz)

PWL (dB)

Computed Based On HW @ Sta. A

Computed Based On HW @ Sta. B

Computed Based On LDV @ Sta. A

Computed Based On LDV @ Sta. B

Measured
NASA/CR—2010-216898/VOL3 5

(a)

(b)

Figure 5.—Effect of fan speed, P&W fan no. 1. (a) Calculations excluding blade noise. 

(b) Calculations including blade noise.

3.0 General Electric 22-in. Diameter Fan

This section describes the validation of BFANS using data acquired from a GE 22-in. fan (designated 

R4) that was tested in the 9- by 15-ft Low Speed Wind Tunnel at NASA Glenn Research Center. The 

experimental data consisted of farfield noise, Laser Doppler Velocimeter (LDV) and hot-wire (HW) 

measurements of the mean velocity and turbulence near the stator leading edge, and total-pressure and 

total-temperature profiles downstream from the fan. Extensive documentation of the testing can be found 

in References 12 through 18.

The flow-field measurements were used in conjunction with CFD calculations to provide the input 

needed to run BFaNS. The BFaNS validation was done at three speeds corresponding to approach, 

 

100

105

110

115

120

125

130

135

140

506380

100125160200250315400500630800

1000125016002000250031504000500063008000

10000

Frequency (Hz)

PWL (dB)

Measured, Approach

Measured, Cutback

Measured, Sideline

Computed, Approach

Computed, Cutback

Computed, Sideline

 

100

105

110

115

120

125

130

135

140

506380

100125160200250315400500630800

1000125016002000250031504000500063008000

10000

Frequency (Hz)

PWL (dB)

Measured, Approach

Measured, Cutback

Measured, Sideline

Computed, Approach

Computed, Cutback

Computed, Sideline
NASA/CR—2010-216898/VOL3 6

cutback, and sideline power. The BFANS calculations were compared to experimental data in terms of 

total sound power spectra.

3.1 Acoustic Configurations

Figure 6 shows the fan configurations that were used during the acoustic tests. The rotor had a 

diameter of 22 in. and consisted of 22 blades. The stator configuration consisted of 54 radial vanes, 26 

radial vanes, 26 swept vanes or no vanes. Reference 15 provides a more detailed description of the 

acoustic setup and farfield noise measurements. Appendix B provides a detailed description of the flow 

path, blade and vane geometry.

3.2 Flow-Field Measurement Configuration

Figure 7 shows the experimental setup used for the LDV and hot-wire measurements. All LDV and 

HW data was acquired with the 26-swept-vane configuration. The HW stations were 2.96 and 5.89 in. 

downstream from the fan trailing edge tip (denoted HW-A and HW-B, respectively). The LDV stations 

were 3.12 and 6.49 in. downstream from the fan trailing edge tip (denoted LDV-A and LDV-B, 

respectively). The downstream HW and LDV stations are close to the leading edge of the radial vanes.

Table 2 lists the LDV and HW data that were used in the present study (shaded cells indicate conditions 

where data was not acquired). Note that hot-wire data acquisition was limited to the approach speed and 

below due to durability problems with the hot wires. Consequently, BFaNS could not be run at cutback or 

sideline power due to the absence of measured turbulence length scales.

 

 Figure 6.—Acoustic configurations, GE fan: (a) 54 radial vanes (baseline); (b) 26 radial vanes; 

(c) 26 swept vanes; and (d) rotor alone.

B

L

A

D

E

V

A

N

E

Centerline

B

L

A

D

E

V

A

N

E

Centerline

B

L

A

D

E

V

A

N

E

Centerline

B

L

A

D

E

V

A

N

E

Centerline

B

L

A

D

E

V

A

N

E

Centerline

B

L

A

D

E

V

A

N

E

Centerline

B

L

A

D

E

Centerline

B

L

A

D

E

Centerline

B=22

V=54 B=22 V=26

B=22

V=26

B=22

(a) (b)

(c) (d)
NASA/CR—2010-216898/VOL3 7

Figure 7.—Flow-field measurement configuration, GE fan.

TABLE 2.—HOT-WIRE AND LDV DATA USED IN PRESENT STUDY, GE FAN

Percent 

design speed

Corrected fan speed 

(rpm)

Acoustic 

condition

HW data at 

station A

HW data at 

station B

LDV data at 

station A

LDV data at 

station B

50 6329 --- No No No No

61.7 7808 Approach Yes Yes Yes Yes

87.5 11074 Cutback --- --- No No

100 12657 Sideline --- --- No No

Appendix B shows plots of the mean and turbulent flow-field measurements acquired at HW and 

LDV Stations A and B. References 13 and 18 provide a detailed description of the HW and LDV data 

acquired.

3.3 Approach Power, 54 Radial Vanes

Figure 8 shows calculated and measured sound power spectra at approach power for the 54-radialvane configuration. The calculations and measurements have been scaled to an 81-in. diameter fan. The 

solid black line excludes blade noise, while the solid red line includes blade noise. The calculated spectra 

are the average of the calculations made with the HW-B and LDV-B data. Unlike the calculations for the 

P&W fan, there was negligible difference between the calculations made with HW or LDV data for the 

GE fan. 

The results for the GE fan are similar to those for the P&W fan. Without blade noise, the calculation 

is in good agreement with the measured spectrum. With blade noise, the calculation exceeds the measured 

spectrum, especially at high frequencies (though the overprediction is much less for the R4 fan compared 

to the P&W fan).

Figure 9 shows calculated and measured sound power spectra at approach power for the rotor-alone 

configuration. The calculations and measurements have been scaled to an 81-in. diameter fan. The flowfield input used for the rotor-alone noise calculation was obtained from CFD predictions provided by 

NASA. The red line indicates rotor self noise, and the blue line indicates rotor turbulent inflow noise. For 

reference, the 54 radial-vane data is included in the figure.

The experimental data shows that the rotor-alone noise is within 3 dB of the 54-radial-vane noise at 

frequencies greater than 5 kHz (i.e., the rotor is more important than the vane at 5 kHz and above). This 

explains the subtle “double hump” in the 54-radial-vane noise spectrum. The first hump is associated with 

vane noise, while the second hump is associated with blade noise. Note that the rotor self-noise 

calculation agrees fairly well with the measured rotor-alone data. Also, based on the calculations, the 

rotor turbulent inflow noise is much less important than the rotor self noise.

B

L

A

D

E

V

A

N

E

Centerline

LDV

Station A

LDV

Station B

HW

Station A

HW

Station B

B

L

A

D

E

V

A

N

E

Centerline

LDV

Station A

LDV

Station B

HW

Station A

HW

Station B
NASA/CR—2010-216898/VOL3 8

Figure 8.—Sound power spectrum, GE R4 fan, 54 radial vanes 

(approach power).

Figure 9.—Sound power spectrum, GE R4 fan, rotor alone (approach 

power).

3.4 Effect of Vane Configuration

Figure 10 shows calculated and measured sound power spectra at approach power for the 54-radialvane, 26-radial-vane and 26-swept vane configurations. The calculations and measurements have been 

scaled to an 81-in. diameter fan. The calculations in Figure 10(b) exclude blade noise, while those in

Figure 10(c) include blade noise. In general, the calculations demonstrate the same trend as the 

experimental data. However, without blade noise, the calculations are more sensitive to the vane 

configuration than the experimental data. With blade noise, the calculations are less sensitive to vane 

noise than the experimental data. These results indicate that BFaNS correctly models the physics of noise 

generation, but may not be able to capture the relative contributions of blade and vane noise.

 

100

105

110

115

120

125

130

135

140

506380

100125160200250315400500630800

1000125016002000250031504000500063008000

10000

Frequency (Hz)

PWL (dB)

Excluding Blade Noise

Including Blade Noise

54 Radial, Measured

 

100

105

110

115

120

125

130

135

140

506380

100125160200250315400500630800

1000125016002000250031504000500063008000

10000

OA

Frequency (Hz)

PWL (dB)

Rotor Self Noise, Predicted

Rotor Inflow Noise, Predicted

Rotor Alone, Measured

54 Radial, Measured
NASA/CR—2010-216898/VOL3 9

(a)

(b)

(c)

Figure 10.—Effect of vane configuration: (a) Experimental data; 

(b) Calculations excluding blade noise; and (c) Calculations

including blade noise.

 

100

105

110

115

120

125

130

135

140

506380

100125160200250315400500630800

1000125016002000250031504000500063008000

10000

Frequency (Hz)

PWL (dB)

54 Radial, Measured

26 Radial, Measured

26 Swept, Measured

 

100

105

110

115

120

125

130

135

140

506380

100125160200250315400500630800

1000125016002000250031504000500063008000

10000

Frequency (Hz)

PWL (dB)

26 Radial, Computed

26 Swept, Computed

54 Radial, Computed

 

100

105

110

115

120

125

130

135

140

506380

100125160200250315400500630800

1000125016002000250031504000500063008000

10000

Frequency (Hz)

PWL (dB)

26 Radial, Computed

26 Swept, Computed

54 Radial, Computed
NASA/CR—2010-216898/VOL3 10

4.0 Boeing 18-in. Diameter Fan

This section describes the validation of BFANS using data acquired from a Boeing 18-in. fan that was 

tested in Boeing’s Low Speed Aeroacoustic Facility (LSAF). The experimental data consisted of farfield 

noise, hot wire (HW) measurements of the mean velocity and turbulence near the rotor and stator leading 

edges, and total-pressure and total-temperature profiles downstream from the fan. Detailed documentation 

of the testing is provided in Ref. 19.

The BFaNS validation was done at three speeds roughly corresponding to 55, 70 and 88 percent of 

the fan design speed. The BFANS calculations were compared to experimental data in terms of total 

sound power spectra.

4.1 Acoustic Configurations

Figure 11 shows the fan configurations that were used during the acoustic tests. The rotor had a 

diameter of 18 in. and consisted of 20 blades. The stator configuration consisted of 60 radial vanes, 30 

radial vanes, 15 radial vanes or no vanes. Reference 19 provides a more detailed description of the 

acoustic setup and farfield noise measurements. Appendix C provides a detailed description of the flow 

path, blade and vane geometry.

4.2 Flow-Field Measurement Configuration

Figure 12 shows the experimental setup used for hot-wire measurements. Station A was 4.3 in. 

downstream from the fan trailing edge tip, and Station B was approximately 1.2 in. upstream from the 

vane leading edge tip. Table 3 lists the HW data that were used in the present study. Reference 19

provides a detailed description of the HW data acquired.

The rig also had the capability to remove the endwall boundary layer at the fan tip. However, all 

BFaNS predictions in this report were performed with the full boundary layer (i.e., no suction). Also, all 

BFaNS predictions were done for the 60-vane configuration, with the low fan loading and small tip 

clearance.

TABLE 3.—HOT-WIRE DATA USED IN PRESENT STUDY, BOEING FAN

Percent design 

speed

Corrected fan speed 

(rpm)

HW data at 

station A

HW data at 

station B

55 9104 Yes Yes

70 11586 Yes Yes

88 14566 Yes Yes

Figure 11.—Acoustic configuration, Boeing fan.

Centerline

B

L

A

D

E

V

A

N

E

B = 20 V = 0, 15, 30 & 60

Centerline

B

L

A

D

E

V

A

N

E

Centerline

B

L

A

D

E

V

A

N

E

B = 20 V = 0, 15, 30 & 60
NASA/CR—2010-216898/VOL3 11

Figure 12.—Flow field measurement configuration, Boeing fan.

Figure 13.—Sound power spectrum, Boeing fan, 55 percent design 

speed (low loading, small clearance).

4.3 55 Percent Design Speed, Low Loading, Small Clearance

Figure 13 shows calculated and measured sound power spectra at 55 percent of design speed. The 

solid black line is the calculation with blade noise. The solid blue line is the calculation without blade 

noise. When blade noise is included, the calculated shape and level are in good agreement with the 

measured data. Without blade noise, the calculation is approximately 2 dB less than the data.

4.4 Effect of Fan Speed, Low Loading, Small Clearance

Figure 14 shows calculated and measured sound power spectra at 55, 70 and 88 percent of design 

speed. The calculations in Figure 14(a) include blade noise, while those in Figure 14(b) exclude blade 

noise. Note blade noise could not be computed at 88 percent of design speed because the tip Mach 

number is supersonic. The results show that BFaNS accurately predicted the shape and level of the 

spectra.

Centerline

A

B

L

A

D

E

B

Centerline

A

B

L

A

D

E

B

 

70

75

80

85

90

95

100

105

110

0 5000 10000 15000 20000 25000

Frequency (Hz)

PWL (dB)

Computed With Blade Noise

Computed Without Blade Noise

Measured
NASA/CR—2010-216898/VOL3 12

(a)

(b)

Figure 14.—Effect of fan speed, Boeing fan (low loading, small clearance): 

(a) Including blade noise; and (b) Excluding blade noise.

5.0 Concluding Remarks

Pratt & Whitney has developed a Broadband Fan Noise Prediction System (BFaNS) for turbofan 

engines. The noise prediction system consists of two computer programs: Setup_BFaNS and BFaNS.

Setup_BFaNS converts user-specified geometry and flow-field information into a BFaNS input file. From 

this input file, BFaNS computes the inlet and aft broadband sound power spectra generated by the fan and 

FEGV. The output file from BFaNS contains the inlet, aft and total sound power spectra from each noise 

source.

This report documents the validation studies that were performed on three fan rigs that were tested 

during the NASA Advanced Subsonic Technology Program (AST). Volume 1 of this report series 

provides instructions for running Setup_BFaNS, and Volume 2 provides instructions for running BFaNS.

 

80

85

90

95

100

105

110

115

120

0 5000 10000 15000 20000 25000

Frequency (Hz)

PWL (dB)

Computed, 55% Speed

Measured, 70% Speed

Measured, 55% Speed

Measured, 70% Speed

Measured, 88% Speed

88%

70%

55%

70%

55%

 

80

85

90

95

100

105

110

115

120

0 5000 10000 15000 20000 25000

Frequency (Hz)

PWL (dB)

Computed, 55% Speed

Computed, 70% Speed

Computed, 88% Speed

Measured, 55% Speed

Measured, 70% Speed

Measured, 88% Speed

88%

70%

55%

88%

70%

55%
NASA/CR—2010-216898/VOL3 13

The validation studies have shown that BFaNS can accurately calculate the shape of the fan 

broadband noise spectra, and can calculate the spectrum level within a couple of decibels of measured 

data. BFaNS can also accurately calculate the effect of fan speed, vane count, and vane sweep. However, 

BFaNS cannot reliably calculate the contribution of blade noise relative to vane noise.

6.0 Recommendations

(1) Due to the empirical nature of the self-noise prediction, BFaNS cannot reliably predict the 

contribution of blade self noise relative to the turbulent inflow noise sources. The current self-noise 

prediction method should be replaced with a method that does not rely on empirical correlations, or one 

that is based on empirical correlations developed for cascade noise rather than isolated airfoil noise.

(2) BFaNS does not account for transmission loss across the rotor or stator. Hanson has recently 

developed this capability (Refs. 20 and 21), and it should be incorporated into BFaNS. This will improve 

the ability of BFaNS to predict the relative contribution of inlet and aft broadband noise.

(3) The cascade response routine in BFaNS is valid only for subsonic flows (i.e., when the incident 

Mach number is less than one). Therefore, BFaNS cannot calculate the noise produced by turbulence 

interacting with supersonic blade tips. This area deserves further attention because most commercial jet 

engines have supersonic blade tips at cutback and sideline power.

(4) The interaction between fan turbulence and the core stator should be added to BFaNS (this is a 

relatively easy enhancement).

(5) The modal content of the noise predicted by BFaNS should be used as input for duct propagation 

codes (CDUCT for example, see Ref. 22). This coupling between source prediction and duct propagation 

will enhance the capability of the aerospace industry to optimize liner designs and reduce noise.

(6) Thus far, BFaNS has been validated on a partial set of data that was acquired during the AST 

program. BFaNS should be thoroughly validated on all the rig data, including the Allison 22-in. fan rig.

BFaNS should also be validated on full-scale engine data, which would require turbulence measurements 

on a full-scale engine.

NASA/CR—2010-216898/VOL3 15

Appendix A.—Pratt & Whitney/NASA Fan Rig Information

Figure A.1—Fan no. 1 rig schematics.

Note: The nose cone shown above does not represent the actual noise-cone geometry used during the test.

It is merely an approximation to facilitate flow-field calculations that were performed on the Fan #1 

configuration.

A.1 Fan No. 1, Flow-Path Geometry File

Flowpath: I.D. wall

35

Axial

 -23.1900 -19.1000 -16.8500 -14.6500 -12.5600 -10.8900

 -9.2300 -7.8640 -6.5970 -5.4480 -4.5480 -3.9350

 -3.3150 -2.6900 -2.0600 -1.1100 -0.5550 0.0000

 0.6650 1.3300 2.2300 3.2400

 3.8900 4.2420 4.6730 5.1700 5.9100 6.7400

 7.8000 10.1000 11.9300 13.7100 15.0900 17.1400

 19.6200

Radius

Centerline

B = 18

CCW rotation

V = 45

B

L

A

D

E

1.482 in 8.226 in - 12.708 in 15.053 in

- 7.708 in

3.74 in

V

A

N

E

Centerline

B = 18

CCW rotation

V = 45

B

L

A

D

E

1.482 in 8.226 in - 12.708 in 15.053 in

- 7.708 in

3.74 in

V

A

N

E

Centerline

B = 18

CCW rotation

V = 45

1.482 in 10.556 in - 12.708 in 15.053 in

- 7.708 in

3.74 in

B

L

A

D

E

V

A

N

E

Station A

4.132 in

Station B

8.152 in

Centerline

B = 18

CCW rotation

V = 45

1.482 in 10.556 in - 12.708 in 15.053 in

- 7.708 in

3.74 in

B

L

A

D

E

V

A

N

E

Station A

4.132 in

Station B

8.152 in

Acoustic 

Configuration

Flow-Field 

Measurement 

Configuration
NASA/CR—2010-216898/VOL3 16

 0.0600 0.0600 0.0600 0.0600 0.0600 0.0750

 0.6350 1.7335 2.6200 3.4120 3.8770 4.1175

 4.3110 4.4620 4.5740 4.6900 4.7090 4.7405

 4.9020 4.9840 4.9750 4.7300

 4.5150 4.4300 4.3870 4.4000 4.4750 4.5750

 4.7000 4.7000 4.7000 4.7000 4.7000 4.7200

 5.2350

Primary Splitter: Duct I.D. wall

30

Axial

 3.7400 3.7407 3.7418 3.7435 3.7452 3.7470

 3.7505 3.7540 3.7575 3.7610 3.7680 3.7750

 3.7820 3.7890 3.7960 3.8030 3.8100

 4.2900 5.2500 5.9900 6.5920 7.4220 8.2260

 8.8780 9.7700 11.2900 12.9700 14.2700 14.8500

 16.5300

Radius

 5.5500 5.5599 5.5656 5.5719 5.5766 5.5805

 5.5869 5.5920 5.5963 5.6000 5.6060 5.6106

 5.6142 5.6168 5.6186 5.6196 5.6200

 5.7850 5.8100 5.8100 5.8100 6.0600 6.3500

 6.4200 6.4750 6.6450 7.1350 7.2850 7.2550

 6.9650

Primary Splitter: Core O.D. wall

30

Axial

 3.7400 3.7407 3.7418 3.7435 3.7452 3.7470

 3.7505 3.7540 3.7575 3.7610 3.7680 3.7750

 3.7820 3.7890 3.7960 3.8030 3.8100

 4.1200 4.5130 4.9030 5.4100 5.9100 6.7400

 7.8000 10.1000 11.9300 13.7100 15.0900 17.1400

 19.6200

Radius

 5.5500 5.5401 5.5344 5.5281 5.5234 5.5195

 5.5131 5.5080 5.5037 5.5000 5.4940 5.4894

 5.4858 5.4832 5.4814 5.4804 5.4800

 5.3100 5.2420 5.2020 5.2050 5.2750 5.3640

 5.4100 5.4100 5.4100 5.5300 5.7350 6.1000

 6.5850

Flowpath: O.D. wall

35

Axial

 -23.1900 -19.1000 -16.8500 -14.6500 -12.5600 -10.8540

 -9.1758 -7.7958 -6.6918 -5.3119 -4.4839 -3.9320

 -3.3800 -2.5520 -2.0000 -1.2796 -0.6530 0.0000

 0.7410 1.4820 2.0700 3.1900

 4.2900 5.3400 5.9900 6.5920 7.4090 8.2260

 8.8700 10.1800 11.4900 12.8000 14.1100 15.0000

 16.5300

Radius

 11.1200 11.1200 11.1200 10.9050 10.5100 10.1270

 10.0915 10.2000 10.3425 10.5575 10.6885 10.7700

 10.8435 10.9330 10.9760 11.0000 11.0550 11.0735

 11.0490 10.9760 10.9850 11.0600

 11.2100 11.3600 11.4000 11.4100 11.3750 11.3100

 11.2900 11.2500 11.2100 11.1650 11.1000 10.9750

 10.7300

A.2 Fan No. 1, Blade Geometry File

LOW NOISE FAN 806 B AERO TD47877-9 SLTO 

 20

'XLE '

4.65548 4.80239 4.94556 5.08495 5.22093 5.35348 

5.90934 6.41638 6.88740 7.32601 7.74196 8.13807 

8.51869 8.88521 9.23982 9.58395 9.91842 10.2435 

10.5587 10.8633 

'YLE '

-.567895 -.588340 -.609174 -.629111 -.648962 -.667595 

-.744498 -.824584 -.904788 -.992043 -1.08189 -1.16632 
NASA/CR—2010-216898/VOL3 17

-1.24253 -1.31212 -1.37652 -1.43886 -1.50221 -1.57272 

-1.65190 -1.72870 

'ZLE '

-1.00811 -1.03756 -1.06347 -1.08875 -1.11289 -1.13349 

-1.20593 -1.25193 -1.28397 -1.30400 -1.29983 -1.28975 

-1.27619 -1.26075 -1.24393 -1.22449 -1.19780 -1.15417 

-1.09281 -1.02071 

'BETA1*ML '

55.7458 54.9105 54.0276 53.2297 52.4571 51.6819 

48.7347 46.6936 44.6492 42.2231 39.6174 37.5233 

35.8931 34.5615 33.3949 32.2920 31.1840 29.9504 

28.6866 27.4006 

'XTE '

4.93962 5.10930 5.26980 5.42266 5.56906 5.70931 

6.27890 6.78156 7.23521 7.65333 8.04079 8.40556 

8.75182 9.08183 9.39724 9.69970 9.99141 10.2808 

10.5657 10.8751 

'YTE '

0.524705 0.517738 0.514805 0.513000 0.512786 0.512125 

0.513708 0.532117 0.572642 0.625699 0.710444 0.804671 

0.894696 0.979065 1.05923 1.13705 1.21706 1.30696 

1.40889 1.51529 

'ZTE '

1.29429 1.32014 1.34422 1.36786 1.39068 1.41338 

1.48889 1.52820 1.54646 1.55607 1.55606 1.54638 

1.53929 1.53107 1.51853 1.50025 1.47267 1.42852 

1.36479 1.28487 

'BETA2* '

76.1635 77.4035 78.2908 79.0146 79.5876 80.0921 

82.0861 83.9269 84.3108 82.0091 78.5042 75.2138 

72.2325 69.4598 66.8028 64.1682 61.4027 58.3470 

54.9446 51.2012 

A.3 Fan No. 1, Vane Geometry File

LOW NOISE FEGV X15 25 sl's slto

 20

'XLE '

5.81543 6.07863 6.35643 6.59566 6.90891 7.18609 

7.43791 7.67066 7.95978 8.23011 8.48556 8.84815 

9.18955 9.51486 9.82664 10.1281 10.4232 10.7192 

11.0326 11.4030 

'YLE '

-.449733 -.430289 -.411172 -.395951 -.377949 -.364261 

-.353612 -.345217 -.336145 -.328454 -.321500 -.311809 

-.303671 -.297059 -.291824 -.288351 -.287275 -.297467 

-.335125 -.415682 

'ZLE '

-.713627 -.728927 -.742346 -.752635 -.764726 -.774127 

-.781648 -.787710 -.794249 -.799586 -.804088 -.809806 

-.814288 -.817782 -.820461 -.822273 -.823108 -.820298 

-.807738 -.773823 

'BETA1*ML '

37.3937 39.0014 40.5328 41.7413 43.1730 44.2960 

45.2044 45.9543 46.7966 47.5311 48.1919 49.0922 

49.8502 50.4856 51.0276 51.4772 51.7887 51.2722 

48.8049 43.2694 

'XTE '

6.32387 6.55653 6.80855 7.02577 7.30814 7.55533 

7.77806 7.98297 8.23775 8.47732 8.70524 9.03119 

9.33987 9.63470 9.91772 10.1917 10.4606 10.7302 

11.0101 11.3128 

'YTE '

0.123309 0.112095 0.101454 0.931932E-01 0.837858E-01 0.770896E-01

0.723298E-01 0.691759E-01 0.659385E-01 0.628574E-01 0.598547E-01 0.551050E-01

0.510384E-01 0.476922E-01 0.449980E-01 0.434292E-01 0.431074E-01 0.477307E-01

0.657158E-01 0.105735 

'ZTE '

0.775949 0.782104 0.786912 0.790609 0.795179 0.799012 

0.802266 0.804980 0.807934 0.810288 0.812156 0.814328 
NASA/CR—2010-216898/VOL3 18

0.815905 0.817067 0.817894 0.818404 0.818659 0.818807 

0.818535 0.815486 

'BETA2* '

96.9231 96.6664 96.3713 96.1203 95.7892 95.5016 

95.2361 94.9556 94.6544 94.4819 94.3689 94.3057 

94.2763 94.2799 94.3256 94.3937 94.5246 94.9275 

95.8411 97.4711 
NASA/CR—2010-216898/VOL3 19

 

 

 

Figure A.2.—Fan no. 1, average velocity, station A.

a. Axial Velocity, LDV b. Axial Velocity, HW

c. Tangential Velocity, LDV d. Tangential Velocity, HW

e. Radial Velocity, LDV (not 

measured)

f. Radial Velocity, HW

g. Total Velocity, LDV h. Total Velocity, HW
NASA/CR—2010-216898/VOL3 20

 

 

 Figure A.3.—Fan no. 1, average velocity, station B.

a. Axial Velocity, LDV b. Axial Velocity, HW

c. Tangential Velocity, LDV d. Tangential Velocity, HW

e. Radial Velocity, LDV (not 

measured)

f. Radial Velocity, HW

g. Total Velocity, LDV h. Total Velocity, HW
NASA/CR—2010-216898/VOL3 21

 

 

 Figure A.4.—Fan no. 1, average turbulence intensity, station A.

a. Axial Turbulence, LDV b. Axial Turbulence, HW

c. Tangential Turbulence, LDV d. Tangential Turbulence, HW

e. Radial Turbulence, LDV (not 

measured)

f. Radial Turbulence, HW

g. Turbulent Kinetic Energy, LDV h. Turbulent Kinetic Energy, HW
NASA/CR—2010-216898/VOL3 22

 

 

 Figure A.5.—Fan no. 1, average turbulence intensity, station B.

a. Axial Turbulence, LDV b. Axial Turbulence, HW

c. Tangential Turbulence, LDV d. Tangential Turbulence, HW

e. Radial Turbulence, LDV (not 

measured)

f. Radial Turbulence, HW

g. Turbulent Kinetic Energy, LDV h. Turbulent Kinetic Energy, HW
NASA/CR—2010-216898/VOL3 23

Figure A.6.—Fan no. 1, average turbulence scale, station A.

Figure A.7.—Fan no. 1, average turbulence scale, station B.

NASA/CR—2010-216898/VOL3 25

Appendix B.—General Electric/NASA Fan Rig Information

Note: The M5 geometry was not available; therefore, noise predictions for the M5 fan were not 

performed

Figure B.1.—R4 fan rig schematics.

Note: The nose cone shown above does not represent the actual noise-cone geometry used during the test. 

It is merely an approximation to facilitate flow-field calculations that were performed on the R4 fan 

configuration.

B

L

A

D

E

V

A

N

E

Centerline

- 6.502 in 1.067 in 8.830 in 17.506 in

- 4.008 in

1.59 in

(assumed splitter LE)

B = 22

CCW rotation

V = 54

B

L

A

D

E

V

A

N

E

Centerline

- 6.502 in 1.067 in 8.830 in 17.506 in

- 4.008 in

1.59 in

(assumed splitter LE)

B = 22

CCW rotation

V = 54

B

L

A

D

E

V

A

N

E

Centerline

- 6.492 in 1.065 in 10.464 in 17.480 in

- 4.001 in

1.59 in

(assumed splitter LE)

B = 22

CCW rotation

V = 26

B

L

A

D

E

V

A

N

E

Centerline

B

L

A

D

E

V

A

N

E

Centerline

- 6.492 in 1.065 in 10.464 in 17.480 in

- 4.001 in

1.59 in

(assumed splitter LE)

B = 22

CCW rotation

V = 26

B

L

A

D

E

V

A

N

E

Centerline

- 6.581 in 1.080 in 13.985 in 17.718 in

- 4.056 in

1.59 in

(assumed

splitter LE)

B = 22

CCW rotation

V = 26

LDV

Station A

4.205 in

LDV

Station B

7.575 in

HW

Station A

4.045 in

HW

Station B

6.975 in

B

L

A

D

E

V

A

N

E

Centerline

- 6.581 in 1.080 in 13.985 in 17.718 in

- 4.056 in

1.59 in

(assumed

splitter LE)

B = 22

CCW rotation

V = 26

LDV

Station A

4.205 in

LDV

Station B

7.575 in

HW

Station A

4.045 in

HW

Station B

6.975 in

54 Radial Vanes

geometry extracted from 

PLOT3D files provided by 

NASA for Broadband 

Challenge

26 Radial Vanes

geometry extracted from 

PLOT3D files provided by 

NASA for Broadband 

Challenge

26 Swept Vanes

geometry extracted from 

PLOT3D files provided by 

NASA for Broadband 

Challenge
NASA/CR—2010-216898/VOL3 26

B.1 R4 Fan, 54 Radial Vanes, Flow-Path Geometry File

Flowpath: Inside Diameter Wall - HUB 

 90

Axial 

 -6.502327 -6.232568 -5.962808 -5.693049 -5.423289

 -5.153530 -4.883770 -4.614011 -4.344251 -4.074492

 -3.804733 -3.534973 -3.265214 -2.995454 -2.725695

 -2.455935 -2.186176 -1.916416 -1.646657 -1.376897

 -1.107138 -0.837379 -0.567619 -0.297860 -0.028100

 0.241659 0.511419 0.781178 1.050938 1.320697

 1.590456 1.860216 2.129975 2.399735 2.669494

 2.939254 3.209013 3.478773 3.748532 4.018291

 4.288051 4.557810 4.827570 5.097329 5.367089

 5.636848 5.906608 6.176367 6.446126 6.715886

 6.985645 7.255405 7.525164 7.794924 8.064683

 8.334443 8.604202 8.873961 9.143721 9.413480

 9.683240 9.952999 10.222759 10.492518 10.762278

 11.032037 11.301796 11.571556 11.841315 12.111075

 12.380834 12.650594 12.920353 13.190113 13.459872

 13.729631 13.999391 14.269150 14.538910 14.808669

 15.078429 15.348188 15.617948 15.887707 16.157467

 16.427226 16.696985 16.966745 17.236504 17.506264

Radius 

 2.250805 2.250757 2.250756 2.250848 2.250945

 2.250903 2.250703 2.251318 2.250003 2.268878

 2.297416 2.373692 2.525183 2.674208 2.791127

 2.900357 3.002891 3.099274 3.189671 3.276292

 3.358367 3.435867 3.509917 3.581078 3.650682

 3.720369 3.794309 3.878063 3.969007 4.067281

 4.170762 4.275789 4.379734 4.479830 4.572974

 4.656779 4.731721 4.799961 4.862569 4.921029

 4.976265 5.029055 5.079441 5.127756 5.173022

 5.214311 5.251548 5.287234 5.322437 5.356940

 5.391048 5.429903 5.478404 5.534245 5.592687

 5.649140 5.699345 5.740850 5.772924 5.795676

 5.810992 5.821017 5.827340 5.831110 5.833467

 5.835088 5.836256 5.836969 5.836978 5.836439

 5.836241 5.837039 5.839078 5.843604 5.850944

 5.859892 5.875535 5.892634 5.916299 5.941113

 5.971357 6.001601 6.037731 6.073982 6.113309

 6.155001 6.196693 6.242894 6.289515 6.336137

Primary Splitter: Inside Diameter Wall - UPPER 

 60

Axial 

 1.590456 1.860216 2.129975 2.399735 2.669494

 2.939254 3.209013 3.478773 3.748532 4.018291

 4.288051 4.557810 4.827570 5.097329 5.367089

 5.636848 5.906608 6.176367 6.446126 6.715886

 6.985645 7.255405 7.525164 7.794924 8.064683

 8.334443 8.604202 8.873961 9.143721 9.413480

 9.683240 9.952999 10.222759 10.492518 10.762278

 11.032037 11.301796 11.571556 11.841315 12.111075

 12.380834 12.650594 12.920353 13.190113 13.459872

 13.729631 13.999391 14.269150 14.538910 14.808669

 15.078429 15.348188 15.617948 15.887707 16.157467

 16.427226 16.696985 16.966745 17.236504 17.506264

Radius 

 4.170762 4.275788 4.379734 4.479830 4.572974

 4.656778 4.731722 4.799960 4.862567 4.921028

 4.976264 5.029056 5.079442 5.127756 5.173022

 5.214311 5.251549 5.287233 5.322438 5.356940

 5.391048 5.429903 5.478404 5.534245 5.592687

 5.649140 5.699345 5.740850 5.772924 5.795675

 5.810993 5.821017 5.827340 5.831110 5.833467

 5.835088 5.836256 5.836969 5.836978 5.836440

 5.836242 5.837039 5.839078 5.843604 5.850944

 5.859892 5.875535 5.892634 5.916299 5.941114

 5.971357 6.001601 6.037731 6.073982 6.113308

 6.155001 6.196693 6.242894 6.289515 6.336136
NASA/CR—2010-216898/VOL3 27

Primary Splitter: Outside Diameter Wall - LOWER

 60

Axial 

 1.590456 1.860216 2.129975 2.399735 2.669494

 2.939254 3.209013 3.478773 3.748532 4.018291

 4.288051 4.557810 4.827570 5.097329 5.367089

 5.636848 5.906608 6.176367 6.446126 6.715886

 6.985645 7.255405 7.525164 7.794924 8.064683

 8.334443 8.604202 8.873961 9.143721 9.413480

 9.683240 9.952999 10.222759 10.492518 10.762278

 11.032037 11.301796 11.571556 11.841315 12.111075

 12.380834 12.650594 12.920353 13.190113 13.459872

 13.729631 13.999391 14.269150 14.538910 14.808669

 15.078429 15.348188 15.617948 15.887707 16.157467

 16.427226 16.696985 16.966745 17.236504 17.506264

Radius 

 4.170762 4.275788 4.379734 4.479830 4.572974

 4.656778 4.731722 4.799960 4.862567 4.921028

 4.976264 5.029056 5.079442 5.127756 5.173022

 5.214311 5.251549 5.287233 5.322438 5.356940

 5.391048 5.429903 5.478404 5.534245 5.592687

 5.649140 5.699345 5.740850 5.772924 5.795675

 5.810993 5.821017 5.827340 5.831110 5.833467

 5.835088 5.836256 5.836969 5.836978 5.836440

 5.836242 5.837039 5.839078 5.843604 5.850944

 5.859892 5.875535 5.892634 5.916299 5.941114

 5.971357 6.001601 6.037731 6.073982 6.113308

 6.155001 6.196693 6.242894 6.289515 6.336136

Flowpath: Outside Diameter Wall - TIP 

 90

Axial 

 -6.502327 -6.232568 -5.962808 -5.693049 -5.423289

 -5.153530 -4.883770 -4.614011 -4.344251 -4.074492

 -3.804733 -3.534973 -3.265214 -2.995454 -2.725695

 -2.455935 -2.186176 -1.916416 -1.646657 -1.376897

 -1.107138 -0.837379 -0.567619 -0.297860 -0.028100

 0.241659 0.511419 0.781178 1.050938 1.320697

 1.590456 1.860216 2.129975 2.399735 2.669494

 2.939254 3.209013 3.478773 3.748532 4.018291

 4.288051 4.557810 4.827570 5.097329 5.367089

 5.636848 5.906608 6.176367 6.446126 6.715886

 6.985645 7.255405 7.525164 7.794924 8.064683

 8.334443 8.604202 8.873961 9.143721 9.413480

 9.683240 9.952999 10.222759 10.492518 10.762278

 11.032037 11.301796 11.571556 11.841315 12.111075

 12.380834 12.650594 12.920353 13.190113 13.459872

 13.729631 13.999391 14.269150 14.538910 14.808669

 15.078429 15.348188 15.617948 15.887707 16.157467

 16.427226 16.696985 16.966745 17.236504 17.506264

Radius 

 11.010941 11.012493 11.013998 11.015268 11.016401

 11.017396 11.018124 11.018691 11.019068 11.019232

 11.019168 11.018869 11.018327 11.017558 11.016528

 11.015241 11.013677 11.011839 11.011221 11.006656

 10.995469 10.981015 10.966768 10.953494 10.940141

 10.926359 10.912204 10.898097 10.884698 10.873096

 10.865967 10.865466 10.870844 10.879611 10.891271

 10.905508 10.922375 10.941645 10.962651 10.984550

 11.006749 11.028477 11.048728 11.067650 11.085357

 11.101904 11.117003 11.130196 11.141621 11.150951

 11.157653 11.160125 11.156557 11.145514 11.127017

 11.104327 11.080913 11.059781 11.042190 11.028078

 11.017560 11.010750 11.006802 11.004715 11.003883
NASA/CR—2010-216898/VOL3 28

 11.003863 11.003966 11.003947 11.003903 11.003971

 11.003982 11.003810 11.003820 11.006583 11.013209

 11.022273 11.036808 11.051996 11.069672 11.087250

 11.104318 11.121385 11.134995 11.148494 11.158052

 11.164576 11.171100 11.168430 11.164928 11.161425

B.1.1 R4 Fan, 54 Radial Vanes, Blade Geometry File

NASA SOURCE DIAGNOSTICS FAN ROTOR AIRFOIL DATA

 51

XLE 

 -3.300717 -3.303915 -3.308069 -3.313466 -3.320478

 -3.329237 -3.340175 -3.353832 -3.370878 -3.392150

 -3.418686 -3.451780 -3.493053 -3.544538 -3.608829

 -3.689264 -3.790090 -3.916614 -4.075167 -4.273249

 -4.520267 -4.828773 -5.215665 -5.700811 -6.305202

 -7.061386 -7.823350 -8.427943 -8.918634 -9.317897

 -9.638566 -9.894466 -10.098216 -10.260604 -10.390247

 -10.493849 -10.576728 -10.643064 -10.696157 -10.738645

 -10.772639 -10.799839 -10.821598 -10.839005 -10.852930

 -10.864068 -10.872978 -10.880105 -10.885588 -10.889806

 -10.893050

YLE 

 0.056513 0.058546 0.061189 0.064622 0.069084

 0.074656 0.081611 0.090283 0.101076 0.114469

 0.131012 0.151285 0.175824 0.204982 0.238555

 0.275329 0.313901 0.353320 0.395976 0.448298

 0.516396 0.600231 0.691755 0.792850 0.932052

 1.099041 1.227651 1.360980 1.423135 1.429222

 1.423645 1.421848 1.426293 1.433713 1.441308

 1.448014 1.453255 1.457092 1.459912 1.462011

 1.463594 1.464802 1.465734 1.466459 1.467026

 1.467472 1.467826 1.468104 1.468316 1.468480

 1.468602

ZLE 

 -1.297397 -1.297990 -1.298759 -1.299756 -1.301048

 -1.302654 -1.304649 -1.307122 -1.310177 -1.313935

 -1.318526 -1.324082 -1.330689 -1.338260 -1.346318

 -1.353738 -1.359192 -1.361348 -1.360299 -1.357423

 -1.351905 -1.338306 -1.312679 -1.274927 -1.226397

 -1.165348 -1.119212 -1.100427 -1.086893 -1.073364

 -1.064533 -1.060213 -1.057601 -1.055210 -1.052501

 -1.049508 -1.046523 -1.043761 -1.041353 -1.039327

 -1.037654 -1.036288 -1.035179 -1.034283 -1.033560

 -1.032978 -1.032511 -1.032136 -1.031847 -1.031624

 -1.031453

BETAT1 

 66.841801 66.815885 66.783103 66.742593 66.683989

 66.614494 66.518115 66.399710 66.240933 66.033458

 65.750624 65.367511 64.835773 64.115349 63.168008

 61.994470 60.685418 59.429298 58.195041 56.664610

 54.802715 53.044276 51.019784 48.935041 46.509141

 43.978135 41.697607 39.574998 38.087785 36.851772

 35.808748 35.100205 34.436097 33.761993 33.149026

 32.648950 32.246985 31.915624 31.643311 31.425093

 31.245763 31.101723 30.986595 30.895777 30.819186

 30.759661 30.714022 30.676131 30.646688 30.624129

 30.608167

XTE 

 -4.088949 -4.092535 -4.097195 -4.103248 -4.111110

 -4.120854 -4.132927 -4.147878 -4.166385 -4.189279

 -4.217576 -4.252514 -4.295610 -4.348718 -4.414104

 -4.494511 -4.593260 -4.714419 -4.862988 -5.045069

 -5.268126 -5.541716 -5.878458 -6.292905 -6.801577

 -7.431083 -8.067842 -8.579360 -8.995760 -9.339889

 -9.620321 -9.846050 -10.027071 -10.172226 -10.288950

 -10.382961 -10.458827 -10.520140 -10.569674 -10.609668

 -10.641939 -10.667974 -10.688969 -10.705896 -10.719543

 -10.730546 -10.739413 -10.746562 -10.752061 -10.756291

 -10.759545

YTE 
NASA/CR—2010-216898/VOL3 29

 0.595555 0.593313 0.590397 0.586604 0.581671

 0.575546 0.567943 0.558513 0.546824 0.532360

 0.514516 0.492602 0.465780 0.433002 0.392969

 0.344221 0.285327 0.214571 0.129390 0.026424

 -0.097081 -0.237919 -0.392177 -0.576410 -0.812905

 -1.075679 -1.269325 -1.430582 -1.533526 -1.565878

 -1.572818 -1.579427 -1.590009 -1.603047 -1.615155

 -1.625258 -1.632740 -1.637674 -1.640837 -1.642914

 -1.644310 -1.645274 -1.645954 -1.646446 -1.646806

 -1.647074 -1.647280 -1.647433 -1.647550 -1.647635

 -1.647700

ZTE 

 1.490532 1.491784 1.493412 1.495524 1.498265

 1.501657 1.505851 1.511032 1.517420 1.525280

 1.534918 1.546681 1.560933 1.578008 1.598115

 1.621252 1.647092 1.675143 1.705382 1.738630

 1.773224 1.795254 1.785352 1.761071 1.718796

 1.631256 1.531697 1.440159 1.362147 1.302295

 1.252064 1.208955 1.174382 1.147466 1.126418

 1.109854 1.096681 1.086109 1.077594 1.070730

 1.065192 1.060726 1.057124 1.054220 1.051879

 1.049991 1.048470 1.047244 1.046300 1.045575

 1.045016

BETAT2 

 123.481562 123.359068 123.200406 122.994211 122.723927

 122.390499 121.977237 121.463885 120.829013 120.048534

 119.084911 117.907573 116.482608 114.764199 112.735775

 110.376564 107.716961 104.740661 101.130447 96.493614

 90.782852 84.861986 79.986424 74.797613 68.264310

 59.838997 53.438499 49.173076 45.258556 43.025379

 42.047168 41.267618 40.301256 39.256656 38.427494

 37.915711 37.615648 37.431940 37.300851 37.201613

 37.121749 37.054726 37.000575 36.955608 36.922670

 36.894472 36.866245 36.849647 36.828629 36.820108

 36.812149

B.1.2 R4 Fan, 54 Radial Vanes, Vane Geometry File

NASA SOURCE DIAGNOSTICS VANE STATOR AIRFOIL DATA

 51

XLE 

 -5.416727 -5.419984 -5.424215 -5.429717 -5.436869

 -5.445656 -5.456452 -5.469716 -5.486012 -5.506033

 -5.530631 -5.560848 -5.597970 -5.643573 -5.699591

 -5.768402 -5.852918 -5.956717 -6.084190 -6.240739

 -6.433002 -6.669145 -6.959180 -7.315404 -7.752908

 -8.290226 -8.827341 -9.264373 -9.619956 -9.909304

 -10.144755 -10.336369 -10.492330 -10.619282 -10.722619

 -10.806724 -10.875172 -10.930878 -10.976212 -11.013106

 -11.043136 -11.067576 -11.087468 -11.103658 -11.116835

 -11.127559 -11.136287 -11.143391 -11.148856 -11.153060

 -11.156293

YLE 

 -0.406363 -0.406194 -0.405973 -0.405686 -0.405312

 -0.404852 -0.404287 -0.403591 -0.402734 -0.401682

 -0.400392 -0.398819 -0.396905 -0.394579 -0.391767

 -0.388400 -0.384440 -0.379891 -0.374796 -0.369099

 -0.362613 -0.354976 -0.345888 -0.335125 -0.322678

 -0.308797 -0.296720 -0.288643 -0.284890 -0.283530

 -0.283985 -0.285139 -0.285764 -0.285726 -0.285371

 -0.285092 -0.285040 -0.285216 -0.285526 -0.285869

 -0.286190 -0.286472 -0.286714 -0.286918 -0.287089

 -0.287229 -0.287347 -0.287443 -0.287516 -0.287574

 -0.287618

ZLE 

 7.267998 7.268016 7.268040 7.268072 7.268112

 7.268163 7.268225 7.268301 7.268394 7.268508
NASA/CR—2010-216898/VOL3 30

 7.268649 7.268822 7.269035 7.269298 7.269619

 7.270013 7.270496 7.271083 7.271793 7.272658

 7.273715 7.275023 7.276612 7.278489 7.280753

 7.283655 7.286515 7.288820 7.290805 7.292380

 7.293630 7.294653 7.295467 7.296127 7.296694

 7.297163 7.297535 7.297823 7.298047 7.298222

 7.298362 7.298473 7.298564 7.298636 7.298696

 7.298744 7.298783 7.298814 7.298839 7.298857

 7.298871

BETAT1 

 131.281769 131.272356 131.246212 131.223061 131.190830

 131.152542 131.100057 131.044341 130.971196 130.874959

 130.761550 130.623424 130.456048 130.250116 129.982424

 129.669266 129.283355 128.854058 128.385733 127.861015

 127.242161 126.511595 125.711721 124.809808 123.857544

 123.024853 122.618754 122.587236 122.795412 123.133131

 123.582709 124.028165 124.490860 124.887123 125.190549

 125.514202 125.867713 126.185061 126.509030 126.772852

 127.005851 127.182839 127.330880 127.471321 127.568032

 127.651582 127.713520 127.773353 127.810731 127.848052

 127.867114

XTE 

 -5.731794 -5.735029 -5.739233 -5.744697 -5.751801

 -5.760493 -5.771126 -5.784135 -5.800049 -5.819518

 -5.843336 -5.872474 -5.908123 -5.951734 -6.005087

 -6.070358 -6.150211 -6.247900 -6.367413 -6.513622

 -6.692492 -6.911319 -7.179029 -7.506539 -7.907212

 -8.397385 -8.887561 -9.288233 -9.615743 -9.883452

 -10.102280 -10.281151 -10.427359 -10.546871 -10.644561

 -10.724414 -10.789686 -10.843039 -10.886650 -10.922299

 -10.951438 -10.975257 -10.994726 -11.010640 -11.023649

 -11.034283 -11.042974 -11.050076 -11.055543 -11.059748

 -11.062981

YTE 

 0.000471 0.000471 0.000471 0.000472 0.000471

 0.000470 0.000470 0.000469 0.000469 0.000468

 0.000469 0.000470 0.000471 0.000473 0.000473

 0.000470 0.000468 0.000469 0.000473 0.000473

 0.000472 0.000471 0.000468 0.000475 0.000471

 0.000464 0.000464 0.000468 0.000471 0.000460

 0.000467 0.000467 0.000462 0.000457 0.000460

 0.000466 0.000469 0.000470 0.000467 0.000464

 0.000463 0.000463 0.000463 0.000463 0.000466

 0.000465 0.000467 0.000467 0.000467 0.000468

 0.000468

ZTE 

 8.809691 8.809727 8.809773 8.809833 8.809911

 8.810006 8.810122 8.810264 8.810437 8.810648

 8.810906 8.811219 8.811600 8.812058 8.812607

 8.813257 8.814007 8.814852 8.815793 8.816864

 8.818124 8.819621 8.821311 8.823187 8.825278

 8.827568 8.829410 8.830547 8.831099 8.831244

 8.831086 8.830804 8.830573 8.830452 8.830420

 8.830431 8.830447 8.830440 8.830409 8.830365

 8.830317 8.830269 8.830224 8.830184 8.830150

 8.830121 8.830096 8.830075 8.830059 8.830048

 8.830036

BETAT2 

 86.977677 86.973932 86.976088 86.973618 86.968883

 86.975419 86.969165 86.970769 86.963695 86.964786

 86.966653 86.968617 86.977814 86.980755 86.998967

 86.987708 86.995244 86.996859 87.022108 87.024978

 87.028719 87.050052 87.087533 87.184788 87.230916

 87.323123 87.347619 87.449030 87.501262 87.537642

 87.590556 87.606019 87.640125 87.669546 87.656125

 87.649347 87.658172 87.670551 87.678676 87.676479

 87.700663 87.709592 87.709429 87.701384 87.694857
NASA/CR—2010-216898/VOL3 31

 87.696417 87.686811 87.693660 87.671975 87.677902

 87.682160

B.2 R4 Fan, 26 Radial Vanes, Flow-Path Geometry File

Flowpath: Inside Diameter Wall - HUB 

 90

Axial 

 -6.492416 -6.223068 -5.953719 -5.684371 -5.415023

 -5.145674 -4.876326 -4.606978 -4.337630 -4.068281

 -3.798933 -3.529585 -3.260236 -2.990888 -2.721540

 -2.452192 -2.182843 -1.913495 -1.644147 -1.374798

 -1.105450 -0.836102 -0.566754 -0.297405 -0.028057

 0.241291 0.510640 0.779988 1.049336 1.318684

 1.588033 1.857381 2.126729 2.396078 2.665426

 2.934774 3.204123 3.473471 3.742819 4.012167

 4.281516 4.550864 4.820212 5.089561 5.358909

 5.628257 5.897605 6.166954 6.436302 6.705650

 6.974999 7.244347 7.513695 7.783043 8.052392

 8.321740 8.591088 8.860437 9.129785 9.399133

 9.668481 9.937830 10.207178 10.476526 10.745875

 11.015223 11.284571 11.553919 11.823268 12.092616

 12.361964 12.631313 12.900661 13.170009 13.439357

 13.708706 13.978054 14.247402 14.516751 14.786099

 15.055447 15.324796 15.594144 15.863492 16.132840

 16.402189 16.671537 16.940885 17.210234 17.479582

Radius 

 2.247375 2.247327 2.247326 2.247418 2.247515

 2.247472 2.247273 2.247887 2.246574 2.265421

 2.293915 2.370075 2.521335 2.670133 2.786873

 2.895937 2.998315 3.094551 3.184809 3.271299

 3.353248 3.430631 3.504568 3.575620 3.645118

 3.714700 3.788526 3.872152 3.962959 4.061083

 4.164406 4.269274 4.373049 4.472974 4.566171

 4.649675 4.724481 4.792390 4.855125 4.913521

 4.968534 5.021084 5.071623 5.119928 5.165138

 5.206371 5.243565 5.279164 5.314289 5.348764

 5.382476 5.416936 5.453929 5.493934 5.537243

 5.583649 5.632728 5.683952 5.736703 5.789956

 5.841779 5.890196 5.933454 5.969981 5.997972

 6.016893 6.028712 6.035462 6.038257 6.038766

 6.039213 6.041073 6.044091 6.047901 6.051907

 6.055678 6.059180 6.062712 6.066678 6.071428

 6.078244 6.087572 6.099421 6.116455 6.138545

 6.164107 6.198385 6.234064 6.280068 6.326072

Primary Splitter: Inside Diameter Wall - UPPER 

 60

Axial 

 1.588033 1.857381 2.126729 2.396078 2.665426

 2.934774 3.204123 3.473471 3.742819 4.012167

 4.281516 4.550864 4.820212 5.089561 5.358909

 5.628257 5.897605 6.166954 6.436302 6.705650

 6.974999 7.244347 7.513695 7.783043 8.052392

 8.321740 8.591088 8.860437 9.129785 9.399133

 9.668481 9.937830 10.207178 10.476526 10.745875

 11.015223 11.284571 11.553919 11.823268 12.092616

 12.361964 12.631313 12.900661 13.170009 13.439357

 13.708706 13.978054 14.247402 14.516751 14.786099

 15.055447 15.324796 15.594144 15.863492 16.132840

 16.402189 16.671537 16.940885 17.210234 17.479582

Radius 

 4.164406 4.269274 4.373049 4.472974 4.566173

 4.649675 4.724481 4.792390 4.855125 4.913521

 4.968534 5.021083 5.071623 5.119929 5.165137

 5.206370 5.243566 5.279164 5.314288 5.348764

 5.382476 5.416936 5.453929 5.493934 5.537243

 5.583649 5.632729 5.683953 5.736702 5.789956

 5.841779 5.890196 5.933453 5.969981 5.997972

 6.016893 6.028712 6.035463 6.038257 6.038766
NASA/CR—2010-216898/VOL3 32

 6.039213 6.041073 6.044092 6.047901 6.051906

 6.055678 6.059180 6.062712 6.066677 6.071427

 6.078244 6.087572 6.099422 6.116455 6.138545

 6.164107 6.198385 6.234063 6.280068 6.326072

Primary Splitter: Outside Diameter Wall - LOWER

 60

Axial 

 1.588033 1.857381 2.126729 2.396078 2.665426

 2.934774 3.204123 3.473471 3.742819 4.012167

 4.281516 4.550864 4.820212 5.089561 5.358909

 5.628257 5.897605 6.166954 6.436302 6.705650

 6.974999 7.244347 7.513695 7.783043 8.052392

 8.321740 8.591088 8.860437 9.129785 9.399133

 9.668481 9.937830 10.207178 10.476526 10.745875

 11.015223 11.284571 11.553919 11.823268 12.092616

 12.361964 12.631313 12.900661 13.170009 13.439357

 13.708706 13.978054 14.247402 14.516751 14.786099

 15.055447 15.324796 15.594144 15.863492 16.132840

 16.402189 16.671537 16.940885 17.210234 17.479582

Radius 

 4.164406 4.269274 4.373049 4.472974 4.566173

 4.649675 4.724481 4.792390 4.855125 4.913521

 4.968534 5.021083 5.071623 5.119929 5.165137

 5.206370 5.243566 5.279164 5.314288 5.348764

 5.382476 5.416936 5.453929 5.493934 5.537243

 5.583649 5.632729 5.683953 5.736702 5.789956

 5.841779 5.890196 5.933453 5.969981 5.997972

 6.016893 6.028712 6.035463 6.038257 6.038766

 6.039213 6.041073 6.044092 6.047901 6.051906

 6.055678 6.059180 6.062712 6.066677 6.071427

 6.078244 6.087572 6.099422 6.116455 6.138545

 6.164107 6.198385 6.234063 6.280068 6.326072

Flowpath: Outside Diameter Wall - TIP 

 90

Axial 

 -6.492416 -6.223068 -5.953719 -5.684371 -5.415023

 -5.145674 -4.876326 -4.606978 -4.337630 -4.068281

 -3.798933 -3.529585 -3.260236 -2.990888 -2.721540

 -2.452192 -2.182843 -1.913495 -1.644147 -1.374798

 -1.105450 -0.836102 -0.566754 -0.297405 -0.028057

 0.241291 0.510640 0.779988 1.049336 1.318684

 1.588033 1.857381 2.126729 2.396078 2.665426

 2.934774 3.204123 3.473471 3.742819 4.012167

 4.281516 4.550864 4.820212 5.089561 5.358909

 5.628257 5.897605 6.166954 6.436302 6.705650

 6.974999 7.244347 7.513695 7.783043 8.052392

 8.321740 8.591088 8.860437 9.129785 9.399133

 9.668481 9.937830 10.207178 10.476526 10.745875

 11.015223 11.284571 11.553919 11.823268 12.092616

 12.361964 12.631313 12.900661 13.170009 13.439357

 13.708706 13.978054 14.247402 14.516751 14.786099

 15.055447 15.324796 15.594144 15.863492 16.132840

 16.402189 16.671537 16.940885 17.210234 17.479582

Radius 

 10.994159 10.995708 10.997211 10.998479 10.999611

 11.000604 11.001331 11.001897 11.002274 11.002436

 11.002373 11.002075 11.001534 11.000766 10.999738

 10.998452 10.996891 10.995056 10.994439 10.989879

 10.978711 10.964280 10.950053 10.936799 10.923467

 10.909705 10.895572 10.881487 10.868108 10.856521

 10.849407 10.848985 10.854277 10.863108 10.874516

 10.888883 10.905819 10.924971 10.945792 10.967818
NASA/CR—2010-216898/VOL3 33

 10.989968 11.011576 11.031997 11.050845 11.068482

 11.085019 11.100056 11.113285 11.124435 11.133971

 11.142259 11.149022 11.153910 11.157242 11.159369

 11.159982 11.158829 11.155923 11.151492 11.145803

 11.138692 11.129869 11.119142 11.106721 11.093042

 11.077677 11.060821 11.043626 11.027036 11.011759

 10.999095 10.990629 10.987237 10.989251 10.995330

 11.005777 11.019678 11.035147 11.052036 11.070549

 11.087467 11.103926 11.119437 11.131994 11.141692

 11.149538 11.152595 11.154867 11.149640 11.144413

B.2.3 R4 Fan, 26 Radial Vanes, Blade Geometry File

NASA SOURCE DIAGNOSTICS FAN ROTOR AIRFOIL DATA

 51

XLE 

 -3.295686 -3.298879 -3.303026 -3.308416 -3.315417

 -3.324162 -3.335084 -3.348720 -3.365741 -3.386981

 -3.413476 -3.446519 -3.487729 -3.539136 -3.603328

 -3.683642 -3.784313 -3.910644 -4.068956 -4.266736

 -4.513378 -4.821414 -5.207716 -5.692122 -6.295592

 -7.050624 -7.811426 -8.415097 -8.905043 -9.303695

 -9.623877 -9.879386 -10.082826 -10.244967 -10.374412

 -10.477855 -10.560608 -10.626843 -10.679855 -10.722278

 -10.756222 -10.783378 -10.805104 -10.822486 -10.836389

 -10.847510 -10.856407 -10.863523 -10.868997 -10.873209

 -10.876449

YLE 

 0.056427 0.058457 0.061095 0.064524 0.068979

 0.074543 0.081487 0.090146 0.100922 0.114295

 0.130812 0.151054 0.175556 0.204670 0.238192

 0.274909 0.313423 0.352781 0.395373 0.447615

 0.515609 0.599317 0.690701 0.791642 0.930631

 1.097366 1.225780 1.358905 1.420966 1.427043

 1.421476 1.419680 1.424119 1.431528 1.439111

 1.445807 1.451040 1.454871 1.457687 1.459782

 1.461363 1.462570 1.463500 1.464224 1.464790

 1.465236 1.465589 1.465866 1.466078 1.466241

 1.466364

ZLE 

 -1.295420 -1.296012 -1.296780 -1.297775 -1.299065

 -1.300669 -1.302661 -1.305130 -1.308180 -1.311932

 -1.316517 -1.322064 -1.328661 -1.336220 -1.344266

 -1.351675 -1.357121 -1.359273 -1.358225 -1.355354

 -1.349844 -1.336267 -1.310679 -1.272984 -1.224527

 -1.163572 -1.117507 -1.098750 -1.085236 -1.071728

 -1.062910 -1.058597 -1.055990 -1.053602 -1.050897

 -1.047908 -1.044928 -1.042170 -1.039766 -1.037743

 -1.036073 -1.034709 -1.033601 -1.032706 -1.031984

 -1.031404 -1.030937 -1.030563 -1.030274 -1.030052

 -1.029880

BETAT1 

 66.841540 66.816244 66.782973 66.742628 66.684322

 66.614716 66.518150 66.399865 66.240827 66.033530

 65.750686 65.367675 64.835810 64.115501 63.168021

 61.994455 60.685341 59.429313 58.194918 56.664497

 54.802421 53.044079 51.019713 48.934801 46.508760

 43.977919 41.697659 39.575252 38.087769 36.851916

 35.809081 35.100383 34.436503 33.762171 33.149025

 32.649496 32.247174 31.915523 31.643164 31.425564

 31.245939 31.101752 30.986446 30.895654 30.819033

 30.759656 30.713830 30.676545 30.646580 30.624292

 30.608500

XTE 

 -4.082717 -4.086298 -4.090950 -4.096994 -4.104844

 -4.114573 -4.126628 -4.141556 -4.160035 -4.182895

 -4.211148 -4.246033 -4.289063 -4.342091 -4.407376

 -4.487660 -4.586259 -4.707234 -4.855577 -5.037379

 -5.260097 -5.533270 -5.869499 -6.283314 -6.791211

 -7.419757 -8.055547 -8.566285 -8.982050 -9.325653

 -9.605659 -9.831043 -10.011789 -10.156722 -10.273268
NASA/CR—2010-216898/VOL3 34

 -10.367136 -10.442887 -10.504106 -10.553565 -10.593498

 -10.625720 -10.651714 -10.672677 -10.689579 -10.703205

 -10.714191 -10.723044 -10.730183 -10.735673 -10.739898

 -10.743147

YTE 

 0.594647 0.592409 0.589497 0.585710 0.580784

 0.574669 0.567078 0.557661 0.545990 0.531549

 0.513732 0.491851 0.465070 0.432342 0.392370

 0.343696 0.284892 0.214244 0.129193 0.026384

 -0.096933 -0.237556 -0.391579 -0.575531 -0.811666

 -1.074039 -1.267390 -1.428401 -1.531188 -1.563492

 -1.570421 -1.577020 -1.587586 -1.600604 -1.612693

 -1.622781 -1.630252 -1.635178 -1.638336 -1.640410

 -1.641804 -1.642767 -1.643445 -1.643936 -1.644296

 -1.644564 -1.644769 -1.644922 -1.645038 -1.645124

 -1.645189

ZTE 

 1.488260 1.489511 1.491136 1.493245 1.495981

 1.499368 1.503556 1.508729 1.515107 1.522955

 1.532579 1.544324 1.558554 1.575603 1.595679

 1.618781 1.644581 1.672590 1.702783 1.735980

 1.770521 1.792518 1.782631 1.758387 1.716176

 1.628770 1.529363 1.437964 1.360071 1.300310

 1.250155 1.207113 1.172592 1.145717 1.124701

 1.108162 1.095009 1.084454 1.075952 1.069098

 1.063569 1.059109 1.055513 1.052613 1.050275

 1.048391 1.046872 1.045648 1.044706 1.043981

 1.043424

BETAT2 

 123.481468 123.359254 123.200188 122.994565 122.724239

 122.390757 121.977183 121.464469 120.828806 120.048482

 119.085037 117.907387 116.482699 114.763998 112.736276

 110.376716 107.717081 104.740096 101.130260 96.493397

 90.782803 84.862107 79.986019 74.797570 68.263904

 59.838861 53.438826 49.173476 45.258485 43.024895

 42.046861 41.267578 40.301317 39.256564 38.427425

 37.915861 37.615470 37.432165 37.300308 37.201853

 37.121897 37.055565 37.000673 36.955570 36.922893

 36.894533 36.866287 36.849766 36.828928 36.820111

 36.812206

B.2.4 R4 Fan, 26 Radial Vanes, Vane Geometry File

NASA SOURCE DIAGNOSTICS VANE STATOR AIRFOIL DATA

 51

XLE 

 -5.356835 -5.360157 -5.364475 -5.370089 -5.377387

 -5.386353 -5.397370 -5.410906 -5.427534 -5.447961

 -5.473057 -5.503883 -5.541746 -5.588244 -5.645342

 -5.715442 -5.801483 -5.907064 -6.036592 -6.195462

 -6.390305 -6.629235 -6.922182 -7.281330 -7.721694

 -8.261791 -8.801073 -9.239424 -9.595829 -9.885674

 -10.121456 -10.313321 -10.469486 -10.596599 -10.700069

 -10.784289 -10.852844 -10.908639 -10.954050 -10.991011

 -11.021088 -11.045566 -11.065489 -11.081700 -11.094894

 -11.105632 -11.114369 -11.121482 -11.126953 -11.131159

 -11.134397

YLE 

 -0.815912 -0.815544 -0.815065 -0.814440 -0.813627

 -0.812628 -0.811398 -0.809889 -0.808038 -0.805765

 -0.802971 -0.799538 -0.795330 -0.790184 -0.783910

 -0.776304 -0.767166 -0.756316 -0.743606 -0.728903

 -0.712053 -0.693055 -0.672365 -0.650916 -0.629767

 -0.609960 -0.595816 -0.589100 -0.587397 -0.588667

 -0.591009 -0.593001 -0.594158 -0.594544 -0.594373

 -0.593860 -0.593188 -0.592481 -0.591817 -0.591215

 -0.590691 -0.590242 -0.589865 -0.589551 -0.589292
NASA/CR—2010-216898/VOL3 35

 -0.589079 -0.588906 -0.588762 -0.588652 -0.588567

 -0.588500

ZLE 

 7.257049 7.257068 7.257093 7.257125 7.257167

 7.257218 7.257281 7.257359 7.257452 7.257568

 7.257712 7.257887 7.258101 7.258362 7.258680

 7.259070 7.259542 7.260114 7.260808 7.261654

 7.262699 7.263993 7.265561 7.267423 7.269702

 7.272570 7.275416 7.277711 7.279691 7.281259

 7.282502 7.283514 7.284327 7.284987 7.285530

 7.285976 7.286336 7.286622 7.286847 7.287024

 7.287163 7.287273 7.287362 7.287434 7.287490

 7.287536 7.287573 7.287602 7.287625 7.287643

 7.287657

BETAT1 

 129.750477 129.739334 129.724029 129.711335 129.690163

 129.665530 129.627791 129.589303 129.534697 129.468759

 129.389145 129.295995 129.175876 129.030101 128.849841

 128.634655 128.374227 128.078744 127.740472 127.359260

 126.954853 126.491982 125.966723 125.376778 124.699379

 123.996106 123.539135 123.403865 123.483888 123.711160

 124.029141 124.390496 124.777101 125.162297 125.546844

 125.924712 126.260976 126.563697 126.826379 127.055075

 127.246984 127.406053 127.541061 127.648344 127.744013

 127.814372 127.877335 127.926293 127.960454 127.987897

 128.006387

XTE 

 -5.968562 -5.971792 -5.975988 -5.981445 -5.988539

 -5.997199 -6.007771 -6.020678 -6.036434 -6.055669

 -6.079152 -6.107820 -6.142817 -6.185543 -6.237701

 -6.301377 -6.379113 -6.474012 -6.589866 -6.731300

 -6.903964 -7.114753 -7.372083 -7.686234 -8.069750

 -8.537947 -9.006143 -9.389659 -9.703811 -9.961140

 -10.171928 -10.344593 -10.486028 -10.601881 -10.696780

 -10.774516 -10.838192 -10.890350 -10.933077 -10.968074

 -10.996741 -11.020225 -11.039460 -11.055216 -11.068122

 -11.078694 -11.087355 -11.094450 -11.099905 -11.104103

 -11.107331

YTE 

 0.000849 0.000848 0.000849 0.000849 0.000849

 0.000848 0.000848 0.000849 0.000849 0.000849

 0.000851 0.000850 0.000850 0.000848 0.000847

 0.000849 0.000849 0.000849 0.000844 0.000838

 0.000838 0.000831 0.000875 0.001030 0.000992

 0.001001 0.000991 0.000989 0.000989 0.000985

 0.000983 0.000990 0.000991 0.000987 0.000987

 0.000995 0.001000 0.000995 0.000991 0.000991

 0.000995 0.000995 0.000994 0.000992 0.000989

 0.000991 0.000989 0.000990 0.000991 0.000992

 0.000993

ZTE 

 10.464846 10.464897 10.464964 10.465050 10.465163

 10.465301 10.465467 10.465672 10.465922 10.466226

 10.466595 10.467046 10.467589 10.468244 10.469028

 10.469959 10.471045 10.472282 10.473650 10.475088

 10.476458 10.477498 10.478033 10.478429 10.478971

 10.478994 10.477524 10.475833 10.473969 10.472043

 10.470109 10.468323 10.466953 10.466063 10.465543

 10.465265 10.465103 10.464980 10.464857 10.464729

 10.464599 10.464472 10.464359 10.464258 10.464171

 10.464100 10.464039 10.463988 10.463948 10.463918

 10.463894

BETAT2 

 87.543584 87.541705 87.539768 87.537604 87.537903

 87.535262 87.531083 87.532151 87.526585 87.529965

 87.534993 87.532980 87.522486 87.499900 87.500703

 87.508280 87.492757 87.482505 87.464872 87.468266
NASA/CR—2010-216898/VOL3 36

 87.456714 87.435190 87.431004 87.438093 87.415635

 87.417438 87.407650 87.418157 87.422962 87.418133

 87.410126 87.400043 87.402715 87.405149 87.408546

 87.391481 87.363950 87.359101 87.372998 87.389326

 87.389493 87.387180 87.397875 87.397881 87.398400

 87.395349 87.389629 87.387746 87.388776 87.378480

 87.377135

B.3 R4 Fan, 26 Swept Vanes, Flow-Path Geometry File

Flowpath: Inside Diameter Wall - HUB 

 90

Axial 

 -6.581012 -6.307988 -6.034964 -5.761940 -5.488917

 -5.215893 -4.942869 -4.669845 -4.396821 -4.123797

 -3.850774 -3.577750 -3.304726 -3.031702 -2.758678

 -2.485655 -2.212631 -1.939607 -1.666583 -1.393559

 -1.120536 -0.847512 -0.574488 -0.301464 -0.028440

 0.244583 0.517607 0.790631 1.063655 1.336679

 1.609702 1.882726 2.155750 2.428774 2.701798

 2.974822 3.247845 3.520869 3.793893 4.066917

 4.339941 4.612964 4.885988 5.159012 5.432036

 5.705060 5.978083 6.251107 6.524131 6.797155

 7.070179 7.343202 7.616226 7.889250 8.162274

 8.435298 8.708322 8.981345 9.254369 9.527393

 9.800417 10.073441 10.346464 10.619488 10.892512

 11.165536 11.438560 11.711583 11.984607 12.257631

 12.530655 12.803679 13.076702 13.349726 13.622750

 13.895774 14.168798 14.441822 14.714845 14.987869

 15.260893 15.533917 15.806941 16.079964 16.352988

 16.626012 16.899036 17.172060 17.445083 17.718107

Radius 

 2.278043 2.277993 2.277993 2.278086 2.278184

 2.278141 2.277939 2.278562 2.277231 2.296334

 2.325218 2.402416 2.555741 2.706569 2.824902

 2.935455 3.039230 3.136779 3.228269 3.315939

 3.399007 3.477445 3.552391 3.624413 3.694859

 3.765390 3.840224 3.924991 4.017037 4.116500

 4.221233 4.327530 4.432723 4.534007 4.628337

 4.713060 4.789160 4.857886 4.921322 4.980497

 5.036348 5.089725 5.141061 5.190151 5.235796

 5.277146 5.315005 5.351330 5.387377 5.421951

 5.453787 5.483371 5.511820 5.540183 5.568631

 5.596844 5.624491 5.651341 5.677274 5.702190

 5.725983 5.748543 5.769778 5.789558 5.807803

 5.824373 5.839240 5.852539 5.864429 5.875103

 5.884788 5.893738 5.902256 5.910888 5.920390

 5.931762 5.946565 5.965664 5.988472 6.014392

 6.043109 6.074581 6.109252 6.146275 6.185302

 6.227963 6.272015 6.317506 6.364912 6.412795

Primary Splitter: Inside Diameter Wall - UPPER 

 60

Axial 

 1.609702 1.882726 2.155750 2.428774 2.701798

 2.974822 3.247845 3.520869 3.793893 4.066917

 4.339941 4.612964 4.885988 5.159012 5.432036

 5.705060 5.978083 6.251107 6.524131 6.797155

 7.070179 7.343202 7.616226 7.889250 8.162274

 8.435298 8.708322 8.981345 9.254369 9.527393

 9.800417 10.073441 10.346464 10.619488 10.892512

 11.165536 11.438560 11.711583 11.984607 12.257631

 12.530655 12.803679 13.076702 13.349726 13.622750

 13.895774 14.168798 14.441822 14.714845 14.987869

 15.260893 15.533917 15.806941 16.079964 16.352988

 16.626012 16.899036 17.172060 17.445083 17.718107

Radius 

 4.221233 4.327531 4.432723 4.534007 4.628337

 4.713060 4.789162 4.857885 4.921322 4.980496

 5.036348 5.089725 5.141060 5.190150 5.235795
NASA/CR—2010-216898/VOL3 37

 5.277147 5.315006 5.351330 5.387377 5.421950

 5.453787 5.483371 5.511820 5.540183 5.568630

 5.596844 5.624491 5.651341 5.677274 5.702190

 5.725983 5.748543 5.769778 5.789558 5.807803

 5.824374 5.839240 5.852539 5.864429 5.875103

 5.884788 5.893738 5.902256 5.910887 5.920390

 5.931762 5.946565 5.965664 5.988472 6.014391

 6.043109 6.074581 6.109251 6.146275 6.185302

 6.227963 6.272015 6.317507 6.364912 6.412795

Primary Splitter: Outside Diameter Wall - LOWER

 60

Axial 

 1.609702 1.882726 2.155750 2.428774 2.701798

 2.974822 3.247845 3.520869 3.793893 4.066917

 4.339941 4.612964 4.885988 5.159012 5.432036

 5.705060 5.978083 6.251107 6.524131 6.797155

 7.070179 7.343202 7.616226 7.889250 8.162274

 8.435298 8.708322 8.981345 9.254369 9.527393

 9.800417 10.073441 10.346464 10.619488 10.892512

 11.165536 11.438560 11.711583 11.984607 12.257631

 12.530655 12.803679 13.076702 13.349726 13.622750

 13.895774 14.168798 14.441822 14.714845 14.987869

 15.260893 15.533917 15.806941 16.079964 16.352988

 16.626012 16.899036 17.172060 17.445083 17.718107

Radius 

 4.221233 4.327531 4.432723 4.534007 4.628337

 4.713060 4.789162 4.857885 4.921322 4.980496

 5.036348 5.089725 5.141060 5.190150 5.235795

 5.277147 5.315006 5.351330 5.387377 5.421950

 5.453787 5.483371 5.511820 5.540183 5.568630

 5.596844 5.624491 5.651341 5.677274 5.702190

 5.725983 5.748543 5.769778 5.789558 5.807803

 5.824374 5.839240 5.852539 5.864429 5.875103

 5.884788 5.893738 5.902256 5.910887 5.920390

 5.931762 5.946565 5.965664 5.988472 6.014391

 6.043109 6.074581 6.109251 6.146275 6.185302

 6.227963 6.272015 6.317507 6.364912 6.412795

Flowpath: Outside Diameter Wall - TIP 

 90

Axial 

 -6.581012 -6.307988 -6.034964 -5.761940 -5.488916

 -5.215893 -4.942869 -4.669845 -4.396821 -4.123797

 -3.850773 -3.577749 -3.304726 -3.031702 -2.758678

 -2.485654 -2.212630 -1.939606 -1.666582 -1.393559

 -1.120535 -0.847511 -0.574487 -0.301463 -0.028439

 0.244585 0.517608 0.790632 1.063656 1.336680

 1.609704 1.882728 2.155751 2.428775 2.701799

 2.974823 3.247847 3.520871 3.793895 4.066918

 4.339942 4.612966 4.885990 5.159014 5.432038

 5.705062 5.978085 6.251109 6.524133 6.797157

 7.070181 7.343205 7.616229 7.889252 8.162276

 8.435300 8.708324 8.981348 9.254372 9.527395

 9.800419 10.073443 10.346467 10.619491 10.892515

 11.165539 11.438562 11.711586 11.984610 12.257634

 12.530658 12.803682 13.076706 13.349729 13.622753

 13.895777 14.168801 14.441825 14.714849 14.987873

 15.260896 15.533920 15.806944 16.079968 16.352992

 16.626016 16.899039 17.172063 17.445087 17.718111

Radius 

 11.144184 11.145755 11.147279 11.148565 11.149713

 11.150718 11.151455 11.152029 11.152410 11.152576

 11.152512 11.152209 11.151661 11.150883 11.149840
NASA/CR—2010-216898/VOL3 38

 11.148537 11.146954 11.145094 11.144468 11.139848

 11.128527 11.113897 11.099478 11.086043 11.072528

 11.058579 11.044253 11.029975 11.016415 11.004662

 10.997435 10.996941 11.002361 11.011303 11.023008

 11.037576 11.054704 11.074055 11.095138 11.117540

 11.139788 11.161870 11.182139 11.202155 11.215710

 11.229100 11.236480 11.242274 11.244181 11.243522

 11.240329 11.235912 11.228514 11.220239 11.210999

 11.201222 11.191209 11.180980 11.170924 11.161669

 11.153554 11.146475 11.141077 11.138075 11.136992

 11.136987 11.137149 11.137113 11.137054 11.137110

 11.137225 11.136878 11.136743 11.139054 11.144890

 11.155511 11.169943 11.185459 11.202701 11.221603

 11.238830 11.255937 11.271424 11.284403 11.294512

 11.301850 11.306308 11.306928 11.303662 11.296490

B.3.5 B-4b. R4 Fan, 26 Swept Vanes, Blade Geometry File

NASA SOURCE DIAGNOSTICS FAN ROTOR AIRFOIL DATA

 51

XLE 

 -3.340660 -3.343895 -3.348099 -3.353562 -3.360659

 -3.369524 -3.380594 -3.394417 -3.411670 -3.433199

 -3.460056 -3.493551 -3.535323 -3.587431 -3.652499

 -3.733908 -3.835954 -3.964009 -4.124481 -4.324960

 -4.574967 -4.887207 -5.278780 -5.769798 -6.381501

 -7.146836 -7.918021 -8.529930 -9.026561 -9.430654

 -9.755203 -10.014200 -10.220415 -10.384768 -10.515981

 -10.620836 -10.704718 -10.771857 -10.825593 -10.868594

 -10.903000 -10.930528 -10.952551 -10.970168 -10.984262

 -10.995536 -11.004554 -11.011766 -11.017315 -11.021585

 -11.024868

YLE 

 0.057197 0.059255 0.061929 0.065404 0.069920

 0.075560 0.082599 0.091376 0.102299 0.115854

 0.132597 0.153115 0.177951 0.207463 0.241442

 0.278660 0.317700 0.357595 0.400768 0.453723

 0.522645 0.607495 0.700126 0.802445 0.943330

 1.112341 1.242507 1.377449 1.440356 1.446517

 1.440873 1.439054 1.443552 1.451062 1.458749

 1.465537 1.470841 1.474725 1.477579 1.479702

 1.481305 1.482528 1.483471 1.484205 1.484778

 1.485230 1.485588 1.485869 1.486084 1.486250

 1.486374

ZLE 

 -1.313097 -1.313697 -1.314476 -1.315485 -1.316792

 -1.318418 -1.320437 -1.322940 -1.326032 -1.329835

 -1.334482 -1.340105 -1.346792 -1.354454 -1.362610

 -1.370120 -1.375640 -1.377821 -1.376760 -1.373849

 -1.368264 -1.354501 -1.328564 -1.290355 -1.241237

 -1.179450 -1.132756 -1.113743 -1.100046 -1.086353

 -1.077415 -1.073043 -1.070400 -1.067979 -1.065237

 -1.062208 -1.059187 -1.056392 -1.053954 -1.051904

 -1.050211 -1.048828 -1.047706 -1.046798 -1.046067

 -1.045478 -1.045005 -1.044626 -1.044333 -1.044108

 -1.043934

BETAT1 

 66.841920 66.816213 66.783037 66.742464 66.684126

 66.614647 66.518016 66.399774 66.240639 66.033436

 65.750527 65.367774 64.835723 64.115307 63.167938

 61.994326 60.685563 59.429369 58.194911 56.664573

 54.802536 53.044212 51.019993 48.934833 46.509207

 43.978321 41.697665 39.574961 38.088167 36.851786

 35.809419 35.100186 34.436220 33.761689 33.148814

 32.649151 32.247034 31.915376 31.642890 31.425661

 31.245482 31.101810 30.986606 30.896034 30.819014

 30.759578 30.713482 30.675800 30.646528 30.624456

 30.608658

XTE 

 -4.138430 -4.142060 -4.146776 -4.152902 -4.160859

 -4.170722 -4.182940 -4.198072 -4.216804 -4.239974
NASA/CR—2010-216898/VOL3 39

 -4.268613 -4.303975 -4.347592 -4.401343 -4.467519

 -4.548899 -4.648844 -4.771470 -4.921836 -5.106120

 -5.331875 -5.608778 -5.949595 -6.369057 -6.883883

 -7.521008 -8.165472 -8.683180 -9.104619 -9.452910

 -9.736737 -9.965199 -10.148410 -10.295321 -10.413456

 -10.508606 -10.585391 -10.647445 -10.697579 -10.738056

 -10.770720 -10.797068 -10.818316 -10.835448 -10.849261

 -10.860396 -10.869372 -10.876607 -10.882173 -10.886454

 -10.889748

YTE 

 0.602761 0.600492 0.597541 0.593703 0.588709

 0.582510 0.574816 0.565271 0.553440 0.538802

 0.520742 0.498563 0.471417 0.438242 0.397724

 0.348386 0.288779 0.217166 0.130956 0.026743

 -0.098256 -0.240798 -0.396923 -0.583385 -0.822741

 -1.088696 -1.284685 -1.447893 -1.552084 -1.584827

 -1.591851 -1.598540 -1.609250 -1.622446 -1.634700

 -1.644926 -1.652498 -1.657492 -1.660693 -1.662795

 -1.664208 -1.665184 -1.665872 -1.666369 -1.666734

 -1.667006 -1.667213 -1.667369 -1.667487 -1.667573

 -1.667639

ZTE 

 1.508569 1.509837 1.511484 1.513622 1.516396

 1.519828 1.524073 1.529317 1.535782 1.543737

 1.553493 1.565398 1.579822 1.597104 1.617454

 1.640871 1.667023 1.695415 1.726019 1.759669

 1.794682 1.816979 1.806956 1.782382 1.739595

 1.650995 1.550232 1.457586 1.378630 1.318054

 1.267215 1.223585 1.188594 1.161352 1.140049

 1.123284 1.109952 1.099252 1.090634 1.083687

 1.078082 1.073562 1.069916 1.066977 1.064607

 1.062697 1.061157 1.059916 1.058962 1.058227

 1.057662

BETAT2 

 123.481490 123.359128 123.199538 122.994199 122.723999

 122.390886 121.977428 121.464103 120.829208 120.048846

 119.085069 117.907460 116.482743 114.764342 112.735963

 110.376617 107.716938 104.740458 101.130253 96.493585

 90.782524 84.861963 79.985831 74.797611 68.264318

 59.839296 53.438460 49.173302 45.258691 43.025093

 42.046849 41.267239 40.301294 39.256844 38.427290

 37.915810 37.615249 37.432006 37.300492 37.201673

 37.122089 37.054914 37.000237 36.955278 36.922331

 36.894595 36.866235 36.849618 36.828841 36.820435

 36.812225

B.3.6 R4 Fan, 26 Swept Vanes, Vane Geometry File

NASA SOURCE DIAGNOSTICS VANE STATOR AIRFOIL DATA

 51

XLE 

 -5.436280 -5.439158 -5.442898 -5.447761 -5.454082

 -5.461904 -5.471583 -5.483561 -5.498379 -5.516716

 -5.539403 -5.567472 -5.602200 -5.645162 -5.698305

 -5.764034 -5.845315 -5.945811 -6.070047 -6.223644

 -6.413625 -6.648677 -6.939284 -7.298377 -7.742211

 -8.290494 -8.838033 -9.280193 -9.637332 -9.925845

 -10.158876 -10.346982 -10.498800 -10.621397 -10.720419

 -10.800375 -10.864911 -10.916997 -10.959044 -10.993000

 -11.020428 -11.042585 -11.060489 -11.074954 -11.086639

 -11.096085 -11.103716 -11.109882 -11.114625 -11.118274

 -11.121081

YLE 

 -0.795390 -0.795226 -0.795011 -0.794732 -0.794368

 -0.793918 -0.793359 -0.792669 -0.791815 -0.790761

 -0.789458 -0.787847 -0.785854 -0.783396 -0.780383

 -0.776725 -0.772351 -0.767202 -0.761226 -0.754169
NASA/CR—2010-216898/VOL3 40

 -0.744985 -0.732126 -0.715833 -0.696765 -0.673254

 -0.647653 -0.624627 -0.605792 -0.590409 -0.577678

 -0.568304 -0.563855 -0.563534 -0.564812 -0.566707

 -0.569411 -0.573070 -0.577260 -0.581446 -0.585243

 -0.588533 -0.591309 -0.593618 -0.595519 -0.597070

 -0.598334 -0.599362 -0.600195 -0.600838 -0.601335

 -0.601717

ZLE 

 7.446051 7.447709 7.449862 7.452662 7.456302

 7.460806 7.466381 7.473278 7.481812 7.492373

 7.505443 7.521616 7.541629 7.566395 7.597041

 7.634959 7.681865 7.739886 7.811643 7.900407

 8.010277 8.146364 8.314905 8.523576 8.781817

 9.101016 9.420207 9.677826 9.886405 10.054845

 10.190549 10.300364 10.389606 10.461797 10.519979

 10.566864 10.604698 10.635252 10.659930 10.679867

 10.695974 10.708991 10.719511 10.728012 10.734879

 10.740430 10.744915 10.748541 10.751328 10.753473

 10.755123

BETAT1 

 129.873150 129.863295 129.848513 129.827107 129.802346

 129.773619 129.736074 129.693068 129.638014 129.568716

 129.481512 129.368901 129.229323 129.064198 128.857568

 128.607673 128.314696 127.973795 127.575615 127.130741

 126.605518 125.962763 125.200603 124.386658 123.410217

 122.396922 121.571660 120.986038 120.658848 120.525876

 120.574000 120.771182 121.134839 121.499509 121.811339

 122.113521 122.448580 122.789434 123.115802 123.399654

 123.642627 123.849998 124.012872 124.147636 124.263409

 124.352260 124.429915 124.487676 124.540279 124.578784

 124.608518

XTE 

 -5.808912 -5.811751 -5.815439 -5.820235 -5.826470

 -5.834159 -5.843640 -5.855333 -5.869753 -5.887536

 -5.909467 -5.936511 -5.969862 -6.010993 -6.061715

 -6.124266 -6.201406 -6.296534 -6.413849 -6.558524

 -6.736938 -6.956962 -7.228297 -7.562913 -7.975567

 -8.484455 -8.993346 -9.405998 -9.740613 -10.011949

 -10.231968 -10.410378 -10.555044 -10.672351 -10.767471

 -10.844597 -10.907134 -10.957841 -10.998956 -11.032294

 -11.059325 -11.081243 -11.099017 -11.113427 -11.125114

 -11.134590 -11.142273 -11.148503 -11.153296 -11.156983

 -11.159819

YTE 

 0.001041 0.001060 0.001082 0.001110 0.001142

 0.001176 0.001206 0.001225 0.001228 0.001215

 0.001204 0.001206 0.001210 0.001206 0.001217

 0.001206 0.001080 0.001023 0.001045 0.001062

 0.001212 0.001035 0.001207 0.001063 0.001136

 0.000984 0.001951 0.002761 0.004607 0.007416

 0.010569 0.014645 0.019606 0.023682 0.027651

 0.032176 0.036805 0.041123 0.045015 0.048511

 0.051551 0.054106 0.056215 0.057949 0.059371

 0.060532 0.061480 0.062252 0.062848 0.063305

 0.063659

ZTE 

 10.909956 10.911592 10.913717 10.916482 10.920075

 10.924505 10.929971 10.936710 10.945022 10.955273

 10.967913 10.983503 11.002730 11.026443 11.055693

 11.091771 11.136288 11.191225 11.259048 11.342788

 11.446181 11.573838 11.731372 11.925663 12.165092

 12.459756 12.754123 12.992770 13.186594 13.343133

 13.469471 13.571556 13.653922 13.720418 13.773914

 13.816706 13.850841 13.878137 13.900045 13.917696

 13.931945 13.943466 13.952789 13.960340 13.966455

 13.971413 13.975430 13.978686 13.981192 13.983118

 13.984600
NASA/CR—2010-216898/VOL3 41

BETAT2 

 86.816576 86.817569 86.820224 86.821634 86.823566

 86.820002 86.824669 86.826677 86.823118 86.815478

 86.806812 86.799077 86.800492 86.800990 86.804042

 86.797891 86.784666 86.789030 86.794510 86.774798

 86.780127 86.771108 86.758127 86.737510 86.717064

 86.699335 86.678051 86.647505 86.672113 86.679102

 86.647844 86.668759 86.674780 86.657714 86.665654

 86.683688 86.682664 86.681759 86.679799 86.662979

 86.641556 86.640914 86.641261 86.636507 86.625623

 86.627781 86.619108 86.613853 86.606500 86.601761

 86.599825
NASA/CR—2010-216898/VOL3 42

 

 

 Figure B.2.—R4 fan, average velocity, station A.

a. Axial Velocity, LDV b. Axial Velocity, HW

c. Tangential Velocity, LDV d. Tangential Velocity, HW

e. Radial Velocity, LDV 

(not measured)

f. Radial Velocity, HW

g. Total Velocity, LDV h. Total Velocity, HW
NASA/CR—2010-216898/VOL3 43

 

 

 Figure B.3.—R4 fan, average velocity, station B.

a. Axial Velocity, LDV b. Axial Velocity, HW

c. Tangential Velocity, LDV d. Tangential Velocity, HW

e. Radial Velocity, LDV (not 

measured)

f. Radial Velocity, HW

g. Total Velocity, LDV h. Total Velocity, HW
NASA/CR—2010-216898/VOL3 44

 

 

 Figure B.4.—R4 fan, average turbulence intensity, station A.

a. Axial Turbulence, LDV

b. Axial Turbulence, HW

c. Tangential Turbulence, 

LDV

d. Tangential Turbulence, HW

e. Radial Turbulence, LDV 

(not measured)

f. Radial Turbulence, HW

g. Turbulent Kinetic Energy, 

LDV

h. Turbulent Kinetic Energy, HW
NASA/CR—2010-216898/VOL3 45

 

 

 Figure B.5.—R4 fan, average turbulence intensity, station B.

a. Axial Turbulence, LDV b. Axial Turbulence, HW

c. Tangential Turbulence, 

LDV

d. Tangential Turbulence, HW

e. Radial Turbulence, LDV

(not measured)

f. Radial Turbulence, HW

g. Turbulent Kinetic Energy, 

LDV

h. Turbulent Kinetic Energy, HW
NASA/CR—2010-216898/VOL3 46

Figure B.6.—R4 fan, average turbulence scale, station A.

Figure B.7.—R4 fan, average turbulence scale, station B.
NASA/CR—2010-216898/VOL3 47

 

 

 Figure B.8.—M5 fan, average velocity, station A.

a. Axial Velocity, LDV b. Axial Velocity, HW

c. Tangential Velocity, LDV d. Tangential Velocity, HW

e. Radial Velocity, LDV (not 

measured)

f. Radial Velocity, HW

g. Total Velocity, LDV h. Total Velocity, HW
NASA/CR—2010-216898/VOL3 48

 

 

 

Figure B.9.—M5 fan, average velocity, station B.

a. Axial Velocity, LDV b. Axial Velocity, HW

c. Tangential Velocity, LDV d. Tangential Velocity, HW

e. Radial Velocity, LDV (not 

measured)

f. Radial Velocity, HW

g. Total Velocity, LDV h. Total Velocity, HW
NASA/CR—2010-216898/VOL3 49

 

 

 Figure B.10.—M5 fan, average turbulence intensity, station A.

a. Axial Turbulence, LDV b. Axial Turbulence, HW

c. Tangential Turbulence, 

LDV

d. Tangential Turbulence, HW

e. Radial Turbulence, LDV 

(not measured)

f. Radial Turbulence, HW

g. Turbulent Kinetic Energy, 

LDV

h. Turbulent Kinetic Energy, HW
NASA/CR—2010-216898/VOL3 50

 

 

 Figure B.11.—R4 fan, average turbulence intensity, station B.

a. Axial Turbulence, LDV b. Axial Turbulence, HW

c. Tangential Turbulence, 

LDV

d. Tangential Turbulence, HW

e. Radial Turbulence, LDV

(not measured)

f. Radial Turbulence, HW

g. Turbulent Kinetic Energy, 

LDV

h. Turbulent Kinetic Energy, HW
NASA/CR—2010-216898/VOL3 51

Figure B.12.—M5 fan, average turbulence scale, station A.

Figure B.13.—M5 fan, average turbulence scale, station B.

NASA/CR—2010-216898/VOL3 53

Appendix C.—Boeing Fan Rig Information

Figure C.1.—Boeing fan rig schematics.

C.1 Geometry Files

C.1.1 Boeing Rig, Flow-Path Geometry File

Flowpath: I.D. wall

29

Axial

 23.1170 23.6230 24.2280 24.8360 25.3450 26.1170

 26.3900 26.7374 27.0848 27.4423 27.7797 28.1271

 28.4745 28.8219 29.1693 29.2500 29.6000 31.0000

 31.4700 35.9000 37.0000 42.5200 49.0000 49.5000

 50.0000 50.5000 51.0000 51.5000 54.7533

Radius

 0.0000 0.9888 1.8864 2.5575 3.0022 3.5163

 3.6200 3.7103 3.7880 3.8532 3.9063 3.9474

 3.9766 3.9942 4.0000 4.0000 4.0000 4.3743

 4.5000 4.5000 4.5000 4.5000 6.9800 7.1900

 7.3400 7.4300 7.4800 7.5000 7.5000

Primary Splitter: Duct I.D. wall

11

Axial

 31.4700 35.9000 37.0000 42.5200 49.0000 49.5000

 50.0000 50.5000 51.0000 51.5000 54.7533

Radius

 4.5000 4.5000 4.5000 4.5000 6.9800 7.1900

 7.3400 7.4300 7.4800 7.5000 7.5000

Primary Splitter: Core O.D. wall

11

Axial

 31.4700 35.9000 37.0000 42.5200 49.0000 49.5000

Centerline

B = 20

CW rotation V = 30 & 60

B

L

A

D

E

28.48 in

35.11 in

4.943 in

45.74 in

23.12 in

29.18 in

V

A

N

E

Centerline

B = 20

CW rotation V = 30 & 60

B

L

A

D

E

28.48 in

35.11 in

4.943 in

45.74 in

23.12 in

29.18 in

V

A

N

E

Centerline

B = 20

CW rotation

B

L

A

D

E

28.48 in

4.943 in

45.74 in

23.12 in

29.18 in

HW

Station

32.78 in

Centerline

B = 20

CW rotation

B

L

A

D

E

28.48 in

4.943 in

45.74 in

23.12 in

29.18 in

HW

Station

32.78 in

Acoustic 

Configuration

Flow Measurement 

Configuration
NASA/CR—2010-216898/VOL3 54

 50.0000 50.5000 51.0000 51.5000 54.7533

Radius

 4.5000 4.5000 4.5000 4.5000 6.9800 7.1900

 7.3400 7.4300 7.4800 7.5000 7.5000

Flowpath: O.D. wall

28

Axial

 4.9429 5.0150 5.1438 5.3966 5.7069 6.0147

 6.4818 7.0105 7.4589 7.9989 26.6700 27.0630

 28.5250 28.9690 29.3790 31.0000 39.9853 40.9935

 41.2438 41.4794 41.7104 41.9961 42.3073 42.9881

 44.0022 44.5470 44.9914 45.7425

Radius

 10.9952 10.6302 10.3620 10.0090 9.7160 9.5257

 9.3174 9.1546 9.0962 9.0625 9.0625 9.0000

 8.7500 8.6700 8.6000 8.6500 8.6500 8.6546

 8.6802 8.7118 8.7800 8.8752 8.9857 9.2302

 9.5895 9.8086 9.9114 10.0073

C.1.2 Boeing Rig, Blade Geometry File

BOEING NOISE RESEARCH FAN ROTOR AIRFOIL DATA

 13

XLE 

 3.561559 3.639948 3.835290 4.130931 4.507303

 4.944070 5.426711 5.961138 6.514472 7.082766

 7.664885 8.259810 8.882345

YLE 

 -.654542 -.671351 -.721084 -.795199 -.888330

 -.988913 -1.079903 -1.152941 -1.219800 -1.269694

 -1.320424 -1.392598 -1.442951

ZLE 

 26.395505 26.409969 26.432180 26.463606 26.498208

 26.543040 26.601611 26.675780 26.748059 26.823387

 26.893716 26.954570 27.020048

BETA1 

 57.857351 56.483573 53.607210 50.185181 46.688229

 43.138043 39.729072 36.696557 34.150685 31.799668

 29.371879 26.976377 23.840608

XTE 

 3.994701 4.061711 4.229500 4.483066 4.805972

 5.180914 5.596003 6.058247 6.540309 7.039913

 7.553667 8.080504 8.640662

YTE 

 .207561 .242441 .326880 .448857 .595086

 .748331 .886733 1.001627 1.098912 1.170944

 1.235934 1.316475 1.375659

ZTE 

 29.179786 29.170911 29.161129 29.141444 29.111954

 29.063591 28.992426 28.898010 28.805873 28.711970

 28.627272 28.556980 28.479465

BETA2 

 79.126653 81.126920 85.814697 87.522874 79.700167

 71.804414 64.544103 57.713709 51.440481 45.963414

 41.375492 37.494574 33.285370

C.1.3 Boeing Rig, Vane Geometry File

BOEING NOISE RESEARCH FAN ROTOR AIRFOIL DATA

 25

XLE 

 4.444516 4.621318 4.797917 4.974300 5.150474

 5.326517 5.502514 5.678491 5.854412 6.030246

 6.205996 6.381669 6.557270 6.732800 6.908259

 7.083648 7.258973 7.434238 7.609443 7.784592

 7.959685 8.134723 8.309708 8.484640 8.659533

YLE 

 -.521443 -.512240 -.503283 -.494939 -.487390

 -.480031 -.472047 -.463123 -.453707 -.444241

 -.434797 -.425355 -.415957 -.406676 -.397607

 -.388840 -.380399 -.372308 -.364638 -.357478
NASA/CR—2010-216898/VOL3 55

 -.350920 -.345039 -.339930 -.335719 -.332129

ZLE 

 33.558464 33.551719 33.545323 33.539482 33.534258

 33.529211 33.523811 33.517896 33.511798 33.505812

 33.499986 33.494304 33.488786 33.483468 33.478388

 33.473574 33.469021 33.464721 33.460687 33.456934

 33.453476 33.450314 33.447460 33.444927 33.442591

BETA1 

 54.377055 54.956615 55.496653 55.957781 56.321473

 56.655262 57.047177 57.528590 58.049527 58.561855

 59.057595 59.539306 60.002626 60.440277 60.842064

 61.198488 61.506767 61.764938 61.965412 62.098746

 62.154838 62.126665 62.004202 61.771489 61.461663

XTE 

 4.449688 4.626422 4.802974 4.979351 5.155568

 5.331666 5.507683 5.683635 5.859512 6.035303

 6.211015 6.386653 6.562220 6.737721 6.913157

 7.088532 7.263849 7.439113 7.614324 7.789486

 7.964601 8.139671 8.314697 8.489683 8.664629

YTE 

 .475292 .463891 .452492 .441234 .430168

 .418995 .407329 .395015 .382252 .369235

 .355987 .342490 .328754 .314802 .300660

 .286336 .271821 .257111 .242207 .227107

 .211805 .196305 .180614 .164646 .148411

ZTE 

 34.973038 34.980243 34.987208 34.993882 35.000271

 35.006563 35.012960 35.019511 35.026069 35.032508

 35.038799 35.044942 35.050921 35.056718 35.062316

 35.067708 35.072895 35.077874 35.082642 35.087198

 35.091547 35.095686 35.099617 35.103363 35.106910

BETA2 

 63.044815 63.938711 64.836718 65.742298 66.660284

 67.595264 68.550815 69.529029 70.529018 71.550060

 72.592986 73.659331 74.749669 75.865051 77.007562

 78.179898 79.384721 80.623190 81.898540 83.215142

 84.578259 85.990699 87.455907 88.989549 89.424262

NASA/CR—2010-216898/VOL3 57

Appendix D.—Turbulence Spectra, GE R4 and M5 Fans

Figure D.1.—Source diagnostic test, R4 fan, approach, station A.
NASA/CR—2010-216898/VOL3 58

Figure D.1.—Continued.
NASA/CR—2010-216898/VOL3 59

Figure D.1.—Continued.
NASA/CR—2010-216898/VOL3 60

Figure D.1.—Concluded.
NASA/CR—2010-216898/VOL3 61

Figure D.2.—Source diagnostic test, R4 fan, approach, station B.
NASA/CR—2010-216898/VOL3 62

Figure D.2.—Continued.
NASA/CR—2010-216898/VOL3 63

Figure D.2.—Continued.
NASA/CR—2010-216898/VOL3 64

Figure D.2.—Concluded.
NASA/CR—2010-216898/VOL3 65

Figure D.3.—Source diagnostic test, M5 fan, approach, station A.
NASA/CR—2010-216898/VOL3 66

Figure D.3.—Continued.
NASA/CR—2010-216898/VOL3 67

Figure D.3.—Continued.
NASA/CR—2010-216898/VOL3 68

Figure D.3.—Concluded.
NASA/CR—2010-216898/VOL3 69

Figure D.4.—Source diagnostic test, M5 fan, approach, station B.
NASA/CR—2010-216898/VOL3 70

Figure D.4.—Continued.
NASA/CR—2010-216898/VOL3 71

Figure D.4.—Continued.
NASA/CR—2010-216898/VOL3 72

Figure D.4.—Concluded.
NASA/CR—2010-216898/VOL3 73

Appendix E.—Turbulence Spectra, P&W Fan Numbers 1 and 2

Figure E.1.—P&W fan number 1 test, approach, station A.
NASA/CR—2010-216898/VOL3 74

Figure E.1.—Concluded.
NASA/CR—2010-216898/VOL3 75

Figure E.2.—P&W fan number 1 test, approach, station B.
NASA/CR—2010-216898/VOL3 76

Figure E.2.—Concluded.
NASA/CR—2010-216898/VOL3 77

Figure E.3.—P&W fan number 1 test, cutback, station B.
NASA/CR—2010-216898/VOL3 78

Figure E.3.—Concluded.
NASA/CR—2010-216898/VOL3 79

Figure E.4.—P&W fan number 1 test, sideline, station A.
NASA/CR—2010-216898/VOL3 80

Figure E.4.—Concluded.
NASA/CR—2010-216898/VOL3 81

Figure E.5.—P&W fan number 1 test, sideline, station B.
NASA/CR—2010-216898/VOL3 82

Figure E.5.—Concluded.
NASA/CR—2010-216898/VOL3 83

Figure E.6.—P&W fan number 2 test, sideline, station A.
NASA/CR—2010-216898/VOL3 84

Figure E.6.—Concluded.
NASA/CR—2010-216898/VOL3 85

References

1. Hanson, D.B., and Horan, K.P., “Turbulence/Cascade Interaction: Spectra of Inflow, Cascade 

Response, and Noise,” Paper No. 98–2319, presented at the AIAA/CEAS 4th Aeroacoustics 

Conference, Toulouse, France, June 2–4, 1998.

2. Hanson, D.B., “Influence of Lean and Sweep On Noise of Cascades With Turbulent Inflow,” Paper 

No. 99–1863, presented at the AIAA/CEAS 5th Aeroacoustics Conference, Seattle, WA, May 10–12, 

1999.

3. Hanson, D.B., “Theory for Broadband Noise of Rotor and Stator Cascade With Inhomogeneous 

Inflow Turbulence Including Effects of Lean and Sweep,” NASA/CR—2001-210762, May 2001.

4. Hanson, D.B., “Theory for Broadband Noise of Rotor and Stator Cascades With Inhomogeneous 

Inflow Turbulence Including Effects of Lean and Sweep,” NASA/CR—2001-210762, May 2001.

5. Glegg, S.A.L., “Airfoil Self Noise Generated in a Cascade,” AIAA Paper 96–1739, presented at the 

2nd AIAA/CEAS Aeroacoustics Conference, State College, PA, May 1996.

6. Glegg, S.A.L., and Jochault, C., “Broadband Self Noise from a Ducted Fan,” presented at the 3rd

AIAA/CEAS Aeroacoustics Conference, Atlanta, GA, May 1997.

7. Glegg, S.A.L, and Jochault, C., “Fan Self Noise Prediction,” Florida Atlantic University Report, April 

1997.

8. Dittmar, J.H., Elliott, D.M., and Bock, L.A., “Some Acoustic Results from the Pratt & Whitney 

Advanced Ducted Propulsor – Fan 1,” NASA/TM—1999-209049, March 1999.

9. Morin, B.L. and Gilson, J., “Analysis of Wake Data for Predicting Broadband Noise from Fan Exit 

Guide Vanes,” United Technologies Research Center, UTRC98–09, August 1999.

10. Morin, B.L., “Broadband Fan Noise Prediction System for Gas Turbine Engines,” AIAA Paper 99–

1889, presented at the AIAA/CEAS 5th Aeroacoustics Conference, Seattle, WA, May 10–12, 1999.

11. Podboy, G.G., Private Communication, Mar 1999.

12. Hughes, C.E., “Aerodynamic Performance of Scale Model Turbofan Outlet Guide Vanes Designed 

for Low Noise,” AIAA–2002–0374, Jan 2002.

13. Podboy, G.G., Krupar, M.J., Helland, S.M., and Hughes, C.E., “Steady and Unsteady Flow Field 

Measurements Within a NASA 22 Inch Fan Model,” AIAA–2002–1033, Jan 2002.

14. Hughes, C.E., Jeracki, R.J., Woodward, R.P., and Miller, C.J., “Fan Noise Source Diagnostic Test -

Rotor Alone Aerodynamic Performance Results,” AIAA–2002–2426, 2002.

15. Woodward, R.P., Hughes, C.E., Jeracki, R.J., and Miller, C.J., “Fan Noise Source Diagnostic Test -

Far Field Acoustic Results,” AIAA–2002–2427, 2002.

16. Heidelberg, L.J., “Fan Noise Source Diagnostic Test—Tone Modal Structure Results,” AIAA–2002–

2428, 2002.

17. Premo, J., and Joppa, P., “Fan Noise Source Diagnostic Test— Wall Measured Circumferential Array 

Mode Results,” AIAA–2002–2429, 2002.

18. Podboy, G.G., “Fan Noise Source Diagnostic Test - LDV Measured Flow Field Results,” AIAA–

2002–2431, 2002.

19. Ganz, U.W., Joppa, P.D., Patten, T.J., and Scharpf, D.F., “Boeing 18-inch Fan Rig Broadband Noise 

Test,” NASA/CR—1998-208704, September 1998.

20. Hanson, D.B., “Broadband Noise of Fans – With Unsteady Coupling Theory to Account for Rotor 

and Stator Reflection/Transmission Effects,” NASA/CR—2001-211136-Revised, November 2001 

(reprinted January 2003).

21. Hanson, D.B., “Broadband Theory for Coupled Fan Stages Including Blade Row 

Reflection/Transmission Effects,” AIAA–2002–2488, presented at the 8th AIAA/CEAS Aeroacoustics 

Conference, Breckenridge, Colorado, June 17–19, 2002.

22. Dougherty, R.P., “A Parabolic Approximation for Flow Effects on Sound Propagation in NonUniform, Softwall Duct,” AIAA 99–1822, presented at the AIAA/CEAS 5th Aeroacoustics 

Conference, Seattle, Washington, May 10–12, 1999.
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)

01-11-2010 

2. REPORT TYPE

Final Contractor Report 

3. DATES COVERED (From - To)

4. TITLE AND SUBTITLE

Broadband Fan Noise Prediction System for Turbofan Engines 

Volume 3: Validation and Test Cases

5a. CONTRACT NUMBER

NAS3-27727 

5b. GRANT NUMBER

5c. PROGRAM ELEMENT NUMBER

6. AUTHOR(S)

Morin, Bruce, L. 

5d. PROJECT NUMBER

5e. TASK NUMBER

5f. WORK UNIT NUMBER

WBS 561581.02.08.03.18.03 

7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)

Pratt & Whitney 

400 Main Street 

East Hartford, CT 06108 

8. PERFORMING ORGANIZATION

 REPORT NUMBER

E-17477-3 

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-2010-216898-VOL3 

12. DISTRIBUTION/AVAILABILITY STATEMENT

Unclassified-Unlimited 

Subject Categories: 71 and 02 

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

This publication is available from the NASA Center for AeroSpace Information, 443-757-5802

13. SUPPLEMENTARY NOTES

14. ABSTRACT

Pratt & Whitney has developed a Broadband Fan Noise Prediction System (BFaNS) for turbofan engines. This system computes the noise generated by turbulence impinging 

on the leading edges of the fan and fan exit guide vane, and noise generated by boundary-layer turbulence passing over the fan trailing edge. BFaNS has been validated on three 

fan rigs that were tested during the NASA Advanced Subsonic Technology Program (AST). The predicted noise spectra agreed well with measured data. The predicted effects 

of fan speed, vane count, and vane sweep also agreed well with measurements. The noise prediction system consists of two computer programs: Setup_BFaNS and BFaNS. 

Setup_BFaNS converts user-specified geometry and flow-field information into a BFaNS input file. From this input file, BFaNS computes the inlet and aft broadband sound 

power spectra generated by the fan and FEGV. The output file from BFaNS contains the inlet, aft and total sound power spectra from each noise source. This report is the third 

volume of a three-volume set documenting the Broadband Fan Noise Prediction System: Volume 1: Setup_BFaNS User’s Manual and Developer’s Guide; Volume 2: BFaNS 

User’s Manual and Developer’s Guide; and Volume 3: Validation and Test Cases. The present volume begins with an overview of the Broadband Fan Noise Prediction System, 

followed by validation studies that were done on three fan rigs. It concludes with recommended improvements and additional studies for BFaNS. 

15. SUBJECT TERMS

Fan blades; Vanes; Broadband; Turbulence; Rotor stator interactions 

16. SECURITY CLASSIFICATION OF: 17. LIMITATION OF

 ABSTRACT

UU 

18. NUMBER

 OF 

 PAGES

95 

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