Daniel L. Sutliff

Glenn Research Center, Cleveland, Ohio

A Mode Propagation Database Suitable for Code 

Validation Utilizing the NASA Glenn Advanced 

Noise Control Fan and Artificial Sources 

NASA/TM—2014-218118

April 2014

AIAA–2014–0719
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Daniel L. Sutliff

Glenn Research Center, Cleveland, Ohio

A Mode Propagation Database Suitable for Code 

Validation Utilizing the NASA Glenn Advanced 

Noise Control Fan and Artificial Sources 

NASA/TM—2014-218118

April 2014

AIAA–2014–0719

National Aeronautics and

Space Administration

Glenn Research Center

Cleveland, Ohio 44135

Prepared for 

SciTech 2014

sponsored by the American Institute of Aeronautics and Astronautics

National Harbor, Maryland, January 13–17, 2014
Acknowledgments

The author would like to acknowledge the efforts of D. Podboy, L. Smith, R. Loew, B. Groening, E. Mysliwiec, and J. Mirecki 

of TFOME for their support in model assembly and testing. This work was supported by the Fundamental Aeronautics, 

Subsonic Fixed Wing Project.

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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 technical management. 
NASA/TM—2014-218118 1

A Mode Propagation Database Suitable for Code Validation 

Utilizing the NASA Glenn Advanced Noise Control 

Fan and Artificial Sources

Daniel L. Sutliff

National Aeronautics and Space Administration

Glenn Research Center

Cleveland, Ohio 44135

Abstract

The NASA Glenn Research Center’s Advanced Noise Control Fan (ANCF) was developed in the 

early 1990s to provide a convenient test bed to measure and understand fan-generated acoustics, duct 

propagation, and radiation to the farfield. A series of tests were performed primarily for the use of code 

validation and tool validation. Rotating Rake mode measurements were acquired for parametric sets of:

(i) mode blockage, (ii) liner insertion loss, (iii) short ducts, and (iv) mode reflection.

1.0 Introduction

The NASA Glenn Research Center (GRC) has been involved in several programs (Advanced 

Subsonic Technology, Quiet Aircraft Technology, and the Fundamental Aeronautics Subsonic Fixed 

Wing) whose goals were the reduction in transport aircraft noise attributed to the turbofan engine. A 

component of turbofan noise (Ref. 1) is the fan noise caused by rotor-stator, and other interactions, 

coupled to duct propagation that radiates to the farfield. Computational aero-acoustic (CAA) codes and 

unique measurement tools are required to enable the development of noise reduction technologies. In 

order to validate these codes and tools, it is necessary to have an acoustic database. 

Parametric studies were performed for several conceptual representations: (i) mode blockage due to 

stator vanes or rotor blades, (ii) liner insertion loss, (iii) the effects of short ducts on radiation, and

(iv) mode reflection due to duct terminations. The intent is not to document specific cases as relevant to a 

modern turbofan but to provide a database for code validation. Nor will a significant portion of the data 

be presented, but rather limited samples. The database was acquired on the Advanced Noise Control Fan

(Refs. 2 and 3) (ANCF) test bed that was built in the early 1990s (Refs. 4 and 5) to evaluate noise 

reduction concepts and to provide databases for CAA code validation. Figure 1 shows the Aero-Acoustic 

Propulsion Laboratory where the ANCF is located and Figure 2 is a photo of the ANCF.

A Configurable Fan Artificial Noise System (CFANS) was utilized to generate and control 

circumferential modes (m). The system consists of four axially distributed rows, each with 16 

circumferentially distributed sets of electromagnetic drivers flush mounted on the inner wall. There are 

two spool pieces, each having two driver rows (see Figure 3). A LabVIEW (National Instruments

Corporation) program is used to generate the waveforms sent to each driver independently, in the proper 

phase relationship to generate the desired circumferential mode. The signals to each row can be adjusted 

globally to effect the radial distribution, if desired. The practical limits of the system are |m-order| ≤ 7, 

and frequency ≤ 1500 Hz. Figure 4 shows the typical high quality output from the CFANS for a sample 

case where mode m = 2 was the target mode generated. The upper row of 3-D “tombstone” plots is at 

480 Hz (equivalent to BPF on ANCF) and the lower row is for 960 Hz (equivalent to 2BPF). The two 

columns represent data from two different builds (limited teardown and reassembly, about one month 

apart) for a limited repeatability demonstration. The target mode is at least 20 dB above any other 

individual mode, and mostly 10 dB above the sum of all other extraneous modes. This is shown in the 

small bar graph above and to the right of the 3-D plot. The repeatability (admittedly limited) is within a 

decibel. Table I provides the modes generated and their cut-off ratios for several hub-to-tip ratios 
NASA/TM—2014-218118 2

(σ) inside the duct, for the studies documented in this paper. The modes were measured by the Rotating 

Rake mode measurement system mounted at the duct radiation plane. The Rotating Rake (Ref. 6) system 

was developed and implemented by GRC in the 1990s to measure turbofan duct acoustic modes. The 

system is a continuously rotating radial microphone rake that is inserted into the duct. It provides a 

complete map of the acoustic duct modes present in a ducted fan. The schematics call out the location of 

the rotating rake measurement location(s), generally at the duct inlet or exit planes. Figure 5 shows the 

propagation angles that are referenced in the relevant sections.

Figure 1.—Aero-Acoustic Propulsion Laboratory Figure 2.—Advanced Noise Control Fan

Figure 3.—Schematic of Configurable Fan Artificial Noise System
NASA/TM—2014-218118 3

TOT—Total Power in Harmonic (all modes)

R/S—Power in Rotor/Stator Interaction Mode

OTH—Power in other modes (non-R/S modes)

Figure 4.—Sample Output of Configurable Fan Artificial Noise System

TABLE I.—MODES GENERATED FOR PARAMETRIC STUDIES USING CFANS 

Cut-off ratios

(σ, hub-to-tip ratio)

Frequency

(Hz)

Modes Inlet 

(σ = 0.0)

R/S 

(σ = 0.375)

Exhaust 

(σ = 0.5)

480 ±(2,0) 1.77 1.89 2.01

“ ” ±(4,0) 1.02 1.03 1.04

580 +(2,0) 2.14

600 +(2,0)/(2,1) 2.21/1.01

700 +(2,0)/(2,1) 2.58/1.17

880 +(2,0)/(2,1)/(2,2) 3.24/1.48/0.99

960 ±(2,0)/(2,1)/(2,2) 3.54/1.61/1.08 3.79/1.72/1.02 4.03/1.53/-

“ ” ±(4,0)/(4,1) 2.03/1.16 2.06/1.22 2.09/1.22

“ ” ±(6,0) 1.44 1.45 1.45
NASA/TM—2014-218118 4

Figure 5.—Schematic of ANCF in Blockage Configurations

2.0 Mode Blockage

2.1 Setup

The objective of this portion of the test was to obtain the effect of geometrical obstructions on mode 

propagation, i.e., blockage (or transmission loss). Blockage effects were measured separately for 

stationary geometry (stator vanes) or for rotating geometry (fan blades). In order to provide a larger 

database, and taking advantage of the flexibility inherent in a no-flow condition, the existing ANCF stator 

vanes were pitched at a range of angles. Geometry of fixed 3-D surfaces prevented pitching the stator 

vanes a full 90°, therefore the tip gap was increased to allow for this rotation. The center-body was 

retained, creating a transition from σ = 0 at the inlet to σ = 0.5 at the exhaust exit plane. These 

configurations are shown schematically in Figure 6 and pictorially in Figure 7.

The baseline case was a clean duct, with no stator vanes or fan blades. A parametric set of modes 

(Table I) were generated at either the forward or aft driver set, and measured by the opposite rotating 

rake. That is: modes generated by the forward driver set were measured by the exhaust rake; modes 

generated by the aft driver set were measured by the inlet rake. Fourteen or 28 stator vanes were installed

at various pitch angles (Table II) and the rake mode measurements repeated. Separately, the rotor blades

were installed at three different pitch angles. The nominal pitch angle for ANCF is 28° and that 

configuration was run at three different fan speeds. The fan pitch angle was changed by ±10° and run at a 

single fan speed for those two angles.

The assumption is made that the source does not change so that the blockage can be computed by 

subtracting the mode PWL measured with stators installed from the mode PWL measured in the clean 

configuration (either with flow or without flow). The configurations were tested over a period of several 

weeks whereby the ambient temperature varied by 10 °F. The mode frequencies generated were at 

constant frequency, corrected to standard day (59 °F). Note that this is standard for duct propagation, but 

does not take into account any changes in the driver response due to changes in actual driver frequency.

2.2 Results

The blockage is defined as the mode amplitude measured by the rotating rake with the duct in the 

clean configuration minus the mode amplitude measured with the desired blockage installed between the 

source and the rake. Thus, a positive number indicates the mode amplitude has been reduced due to 

blockage.

Figure 8 shows the results for mode blockage at various stator vane configurations for modes at 480 

and 960 Hz. The blockage for the forward propagating direction (generated by the aft drivers, propagation 

through the obstruction, and measured by the inlet rake) is shown in Figure 8(a) (480 Hz) and Figure 8(b)

(960 Hz).
NASA/TM—2014-218118 5

(a) Clean Duct

Modes generated by driver 

spools are measured at 

opposite rake.

Assumption is source does 

not change with the

insertion of blockage or the 

addition of flow.

(b) Stationary Blockage

(c) Rotating Blockage

Figure 6.—Schematic of ANCF in Blockage Configurations
NASA/TM—2014-218118 6

TABLE II.—BLOCKAGE CONFIGURATIONS TESTED

(a) Stator vane configurations

14 vanes 28 vanes

-------------------------- α=20°

α=45° α=45°

α = 45° ~ δ = 1.63 in. α = 45° ~ δ = 1.63in.

α = 90° ~ δ = 1.63 in. --------------------------

Designation: Pitch Angle (α) ~ tip gap (δ)

(b) Fan blade configurations

θ = 18° (1800 Ω)

θ = 28° (0, 900, 1800 Ω)

θ = 38° (900 Ω)

(a) Clean Duct Configuration (b) 28 Vane—45° Pitch Configuration

Figure 7.—Photos of ANCF in Mode Blockage Configurations

Figure 8.—Circumferential Mode Blockage Levels from Stator Vanes
NASA/TM—2014-218118 7

Figure 9.—Circumferential Mode Blockage Levels from Rotor Vanes

The case labeled clean is actually the difference between two clean cases several weeks apart. As 

such it can provide an estimate of the significance for a measured blockage value. This number is about 

±1 dB. Anything less than that cannot be assumed to be a result relevant to blockage.

Little blockage is seen at low m-orders in either direction. These modes’ circumferential propagation 

angles are relatively low as a result of their higher cut-off ratio. The higher order circumferential modes 

(four at 480 Hz, six at 960 Hz) are significantly blocked as a result of their higher circumferential 

propagation angles (Ψθ)—see Figure 5(a). The stator vane count is seen to increase the mode blockage 

levels. Thus, it appears as if projected area is the biggest influence on blockage levels under these 

conditions.

Blockage levels obtained with the rotor (alone) at various rotor RPM (Ω) and pitch angles (α) are 

shown in Figure 9. 

3.0 Liner Evaluation

3.1 Set-Up

Figure 10 shows the schematic of the ANCF configuration for the evaluation of insertion loss due to a 

liner. The liner used was a single-degree-of-freedom (SDOF) liner with a screen mesh on a 34 percentopen-area (POA). The normalized design resistance for the liner is 1.7ρc. The liner core depth is 0.85 in.; 

resonance frequency is 3221 Hz.

The rotating rake ring was installed in one of two locations: upstream (Figure 10(a)) of the liner to 

measure the modal PWL at the entrance, and downstream (Figure 10(b)) of the liner to measure the modal

PWL at the liner exit. Comparing the two results in liner insertion loss (positive number indicates 

attenuation). These rake configurations were tested for both the liner exposed and taped over (to provide a 

hard-wall baseline).

3.2 Results

Figure 11 shows the mode PWLs measured at the entrance and the exit for the hard-wall and the liner.

Figure 11(a) shows that at BPF the insertion loss is minor—not surprising as this frequency was not the 
NASA/TM—2014-218118 8

design frequency. Note that in general the comparison of the mode strength at the entrance to the HW is 

comparable to the mode strength at the entrance of the liner. An exception is that mode 4 HW to SW 

entrance comparison shows a huge variation in PWL. This is thought to be due to being close to cut-off 

and being more susceptible to reflections. Figure 11(b) shows the insertion loss at 960 Hz, near the target 

design of the liner. The attenuation is much greater, and increases as the mode number increases. This is 

expected as the higher mode numbers have lower cut-off ratios—it is generally accepted that liners are 

more effective at cut-off ratios near unity (Ref. 7) since the mode angle is propagating into the liner (see 

Figure 5(b)). 

(a) Entrance Measurement Plane

(b) Exit Measurement Plane

Figure 10.—Schematic of Liner Configurations Tested

 
NASA/TM—2014-218118 9

(a) 480 Hz (b) 960 Hz

Figure 11.—Liner Configurations Results

4.0 Short-Duct Effects

Duct mode propagation theory assumes a long duct as defined by the Length to Diameter ratio 

(L/D > 1) in order for the classic mode structure to develop along the predicted analytical forms. In 

reality, even a cut-off mode can be said to “propagate” from the source, albeit at a significant decay rate. 

Modes that are well below cut-on may decay at a rate of 80 to 100 dB per duct diameter, while a mode 

just below cut-on may decay at a rate of only 2 to 3 dB per diameter (Ref. 8).

4.1 Set-Up 

To investigate this effect, the ANCF/CFANS was tested in two duct lengths, with the actuated driver 

row 1 diameter from the duct exit, and 1/4–diameter from the duct exit (Figure 12). The modes were 

measured at the inlet entrance plane. The duct exit was filled with absorptive material to prevent 

reflections as well as farfield contamination from duct aft radiation. For this portion of the test, 

corresponding far-field directivity data were acquired. The farfield array was kept at a constant distance

from duct inlet entrance plane.

4.2 Results

Typical in-duct mode results for the two duct lengths are shown in Figure 13. The generated mode 

was m = +2 or m = –2. Figure 13(a) shows the modal decomposition. For the long duct all of the 

“extraneous” modes have decayed to the measurement floor ~ 75 to 80 dB. The modes in the short duct 

configuration have not decayed, nearly equal in strength to the target mode. Figure 13(b) illustrates this 

by comparing the total PWL in all modes, PWL in the generated mode, and the sum of the non-target 

mode. For the long duct the majority of the power is in the target mode, for the short duct the extraneous 

modes carry more energy.

The effect in the far-field indicates that the modes measured at the inlet plane do in fact propagate to 

the farfield. Figure 14 shows the tonal directivity for m = ±2. The long duct directivity shows the 

characteristic flat lobe associated with a well cut-on mode. Note the symmetry between the positive and 

negative mode. The pattern radiated from the short duct shows significant departure from the classical 

directivity. It also shows an asymmetry between the positive and negative generated mode. These effects 

are due to axisymmetric variation (Ref. 9) resulting from multiple modes.
NASA/TM—2014-218118 10

(a) Long Duct, L/D = 1

(b) Short Duct, L/D = 1⁄4

Figure 12.—Effect of Duct Length on In-Duct Modes

(a) Individual Modes (b) Modal Summation

Figure 13.—Effect of Duct Length on In-Duct Modes
NASA/TM—2014-218118 11

Figure 14.—Effect of Duct Length on Far-field Directivity

5.0 Mode Reflection

5.1 Setup

In order to provide a clean, cylindrical duct, for this experiment the ANCF was built up off of the 

stanchion that normally supports the fan and duct sections that make up the nacelle. That is, the spool 

pieces were stacked up in a vertical orientation based on the floor. This removed center-body and support 

pylon from the arrangement, providing a constant area cylindrical duct. Two configurations were tested in 

this setup: (a) with the flow lip attached, and (b) without the flow lip attached, which left a bare flange as 

the exit termination (Figure 15 and Figure 16). The entire stack rested on the floor, and approximately 

6 in. of foam material was placed in the bottom of the stack to minimize reflections from the floor.

Typically, a single rake, extending from the outer-wall to the duct centerline, has been mounted to 

measure duct modes. It has been known (Refs. 10 and 11) that measuring at a single axial location will 

not be able to account for reflections in the duct, therefore, for this experiment an additional rake was 

mounted on the same rotating ring as the original. This second rake was adjustable in the axial direction 

over the range of 2.5- to 10.5-in., in fixed, 1-in. increments, and was mounted 180° in the circumferential 

direction from the original rake, which remains fixed in the axial direction. Figure 17(a) and Figure 17(b)

show this arrangement.

Data were acquired from the dual rakes in order to provide the two-point axial variation needed to 

compute the reflection. Reflections were created using two methods. The first method relies on the natural 

reflections due to an open-ended exit termination. The ring containing the dual rotating rake system was 

mounted at the exit of the ANCF stack-up (Figure 15(a)). The single driver row (C) farthest from the exit 

termination was used to generate the modes in Table I. This configuration was run with the flow lip 

attached—this was assumed to minimize reflections, and with the flow lip removed, creating a sharp 90° 

flanged exit—this was assumed to create reflections. A second configuration was used to generate 

artificial reflections, see Figure 15(b). This was accomplished by locating the dual rake ring in the center 

of the stack-up. Driver row C was used to generate the “primary” wave and driver set B was used to 

generate the “reflected” wave. Each driver row was actuated independently and the modes were measured 

by the dual rakes. Then both sets were activated simultaneously and the resulting superposition was 

measured. 
NASA/TM—2014-218118 12

(a) Termination Reflection Configuration (b) Artificial Reflection Configuration

Figure 15.—ANCF in Mode Reflection Configurations

(a) With flow lip attached (b) With flow lip removed 

Figure 16.—ANCF in Off-Stanchion Configuration

The concept is that the measured combination B + C is the resulting superimposed mode and is equal 

to B+C measured independently and mathematically combined. Thus any technique to separate the 

“primary” from the “reflected” wave will result in B and C that can be compared to the independent 

measurements for code validation (B and C are arbitrary amplitudes generated by driver rows B and C). 
NASA/TM—2014-218118 13

(a) Second Rotating Rake with Extensions (b) Close-up of Rotating Rake Separation

Figure 17.—Dual Rakes on Same Rotating Ring 

This assumes that there are no other reflections, either from the duct exit, the anechoic termination, or the 

rakes themselves. It also assumes that the driver rows generate the same mode PWL (magnitude and 

phase) independently and when combined. It also assumes that the rake response is independent of the 

mode propagation direction.

5.2 Results

The dual rake measurements were evaluated to determine if the basic assumptions were correct. Data 

from each rake were acquired when installed separately, in each of the two circumferential locations, in a 

reverse orientation, and with both rakes installed so that the adjustable upstream rake blocked the fixed 

rake. Table III shows these results. In general the results agree to within a decibel. 

Figure 18 shows typical results from the dual rake measurements. The fixed rake mode PWLs are 

compared to the adjustable rake levels as a function of separation distance. Figure 18(a) is data at 480 Hz 

where a single radial mode is cut on; Figure 18(b) shows data at 960 Hz where three radial modes are cuton. The flow-lip on and flow-lip off cases are compared. The data show that the mode PWL variation in 

axial distance is greater with the flow-lip removed, indicating a stronger reflection, due to constructive 

and destructive interference, as expected. Note also that the fixed rake measurements are constant as the 

movable rake is adjusted (also as expected).

TABLE III.—MODE PWLS FOR A RANGE OF MODES, FREQUENCIES, AND RAKE ORIENTATIONS

PWL 

in dB

Fixed rake

0° position

Standard orientation

Fixed rake

180° position

Standard orientation

Fixed rake

0° position

Reverse orientation

Extended rake

180° position

Standard orientation

Fixed rake blocked

0° position

Standard orientation

1BPF

(2,0) 116.5/116.2 116.9/116.8 116.6 116.1 116.1

(4,0) 99.1/98.1 98.7/98.0 98.1 98.9 98.2

2BPF

m = 2 113.7/113.3 113.0/113.3 113.5 112.7 113.3

(2,0) 106.0/105.6 105.7/105.6 105.2 105.1 105.5

(2,1) 108.5/107.7 107.3/107.2 108 106.4 107.8

(2,2) 110.9/110.8 110.4/111.0 111 110.5 110.8

m = 4 112.9/112.3 112.3/112.3 112.3 111.8 112.4

(4,0) 109.2/108.4 108.8/108.8 108.3 108 108.5

(4,1) 110.4/110.0 109.7/109.8 110.1 109.4 110.2

(6,0) 113.7/112.4 112.9/112.9 113.2 112.3 112.7
NASA/TM—2014-218118 14

Figure 18(c) shows a sample of the data from the dual-row configuration. In this sample, m = 2 was 

generated and the rakes were separated axially by 6.5 in. The amplitude of driver row C was held 

constant. The amplitude of driver row B was varied to simulate variation of the strength of the 

“reflection” from 1.0 to 0.25. This is indicated on the plot by “G”; the ratio of the driver row B amplitude 

to driver row C amplitude. The mode PWL from each row actuated alone and together is presented. 

Variations in the sum B + C are seen as the strength of the artificially generated reflection is modified.

(a) 480 Hz—Termination Reflection

(c) 480 Hz—Artificial Reflection

(b) 960 Hz—Termination Reflection

Figure 18.—Changes in Mode Levels with Axial Distance (m=+2)
NASA/TM—2014-218118 15

6.0 Conclusion

Parametric sets of mode propagation databases were acquired for the purpose of computational aeroacoustic and acoustic measurement tool validation. Limited samples of the data were presented and 

analysis limited to ensuring the database is valid relative to basic acoustic concepts. The complete data 

and geometry referred to in this paper are available upon request.

References

1. Hubbard, H.H., ed., Aeroacoustics of Flight Vehicles: Theory and Practice: Volume 1, NASA 

Reference Publication 1258, Vol. 1, WRDC Technical Report 90-3052.

2. Loew, R.A., Lauer, J.T., McAllister, J., and Sutliff, D.L., “The Advanced Noise Control Fan,”

NASA/TM—2006-214368, also AIAA–2006–3150, Nov. 2006.

3. McAllister, J., Loew, R.A., Lauer, J.T., and Sutliff, D.L., “The Advanced Noise Control Fan Baseline 

Measurements,” NASA/TM—2009-215595, also AIAA–2009-0624, Oct. 2009.

4. Heidelberg, L.J., Hall, D.G., Bridges, J.E., and Nallasamy, N., “A Unique Ducted Fan Test Bed for 

Active Noise Control and Aeroacoustics Research,” NASA TM–107213, also AIAA–96–1740.

5. Sutliff, D.L., Nallasamy, N., and Elliott, D.M., “Baseline Acoustic Levels of the NASA Active Noise 

Control Fan Rig,” NASA TM–107214, also AIAA–96–107214.

6. D.L. Sutliff. “Rotating Rake Turbofan Duct Mode Measurement System,” International Journal of

Aeroacoustics, June 2007. 

7. Rice, Edward, J., “Spinning Mode Sound Propagation in Ducts with Acoustic Treatment,” NASA TN 

D-7913, May 1975.

8. Tyler, J.M and Sofrin, T.G., “Axial Flow Compressor Noise Studies,” SAE Transactions, Vol. 70, 

1962.

9. Heidelberg, L.J., Sutliff, D.L., and Nallasamy, M., “Azimuthal Directivity of Fan Tones Containing 

Multiple Modes,” NASA TM-107464, AIAA 97-1587.

10. Hall, D. G., Heidelberg, L., and Konno, K., “Acoustic Mode Measurements in the Inlet of a Model 

Turbofan Using a Continuously Rotating Rake: Data Collection/Analysis Techniques,” AIAA Paper 

No. 93-0599, 1993.

11. Cicon, D.E. and Sofrin, T.G., “Method for Extracting Forward Acoustic Wave Components from 

Rotating Microphone Measurements in the Inlets of Turbofan Engines,” NASA CR-195457, April 

1995. 
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Subject Categories: 07, 09, and 71

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

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

13. SUPPLEMENTARY NOTES

14. ABSTRACT

The NASA Glenn Research Center’s Advanced Noise Control Fan (ANCF) was developed in the early 1990s to provide a convenient test

bed to measure and understand fan-generated acoustics, duct propagation, and radiation to the farfield. A series of tests were performed

primarily for the use of code validation and tool validation. Rotating Rake mode measurements were acquired for parametric sets of: (i)

mode blockage, (ii) liner insertion loss, (iii) short ducts, and (iv) mode reflection.

15. SUBJECT TERMS

Aeroacoustics; Ducted fans; Fan noise; Test

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