■■

AFAPL-TR.70-80

O ^5

PERFORMANCE AND ACOUSTIC TESTING OF A VARIABLE CAMBER PROPELLER

DONALD P. McERLEAN. 1ST LIEUTENANT. USAF DONALD E. EDWARDS

TECHNICAL REPORT AFAPL-TR-70-80

FEBRUARY 1971

D D C fpnnOEJ

jim 3 1971

E©E[nnsu

—^B, This document has been approved for public release

and sale; its distribution is unlimited.

AIR FORCE AERO PROPULSION LABORATORY AIR FORCE SYSTEMS COMMAND

WRIGHT-PATTERSON AIR FORCE BASE OHIO

^

■

■^■W"!1 -«■■'W-1-1--'11*"'1"''""'"'"

UNCLASSIFIED Security Cl«»>ific»tion

DOCUMENT CONTROL DATA R&D (Security ctmamlflemHon of fltfg» body of mbitrmct mnd Indmxtng mmotmtltm must be T red when the ovmratl report Is clmmmlilBd) I. ORIGINATING ACTIVITY (Corporate author) \za. REPORT SECURITY CLASSIFICATION

Air Force Aero Propulsion Laboratory Wright-Patterson AFB, Ohio

UNCLASSIFIED 2b. GROUP

S. REPORT TITLE

PERFORMANCE AND ACOUSTIC TESTING OF A VARIABLE CAMBER PROPELLER

4. DESCRIPTIVE NOTE* (Type o I report and Inelualve date»)

Work period from March 1970 through July 1970 B- AUTHOR(S) (F/r»f n«m», middle Initial, laet name)

Donald P. McErlean, 1st Lieutenant, USAF Donald E. Edwards

• . REPORT DATE

February 1971

J>

•a. CONTRACT OR GRANT NO.

6. PROJECT NO. 3066

«.Task No. 306612

7a. TOTAL NO. OF PAGES

98 7b. NO. OF REFS

»A. ORIGINATOR'S REPORT NUMBERIS)

AFAPL-TR-70-80

>b. OTHER REPORT NO(f) (Any other numbers that may be aeelgned thle report)

10. DISTRIBUTION STATEMENT

This document has been approved for public release and sale; its distribution is unlimited.

II. SUPPLEMENTARY NOTES 12. SPONSORING MILITARY ACTIVITY

Air Force Aero Propulsion Laboratory Wright-Patterson AFB, Ohio

\

-This report presents the test results obtained from a series of performance and acoustic near-field measurements on a propeller fitted with a variable camber feature. The subject propeller^ manufactured by the Detroit Diesel Allison Division of General Motors under a prior Contributing Engineering Program Contract, effects a change in camber by deflecting a flap positioned along the 72% chordal line of each blade.

The tests were conducted on the 10,000 horsepower electric whirl rig located at Wright- Patterson Air Force Base. In comparison with the same blade v/ith fixed camber, the variable camber feature increased the static thrust by approximately 11% with a horsepower input of 3500 SHP at 1020 RPM. The overall sound pressure level and the 1/3 octave band frequency spectra did not appear to be appreciably influenced by increasing the camber on this propeller.

These tests represent the only test data available on this unique propeller configuration which good potential for V/STOL applications.

v

DD FORM 1473 UNCLASSIFIED Security Classification

i \

UNCLASSIFIED Security"Clas8incation

KEV WORDS ROLE | WT

Propellers for Aircraft Variable Camber V/STOL Aircraft Static Performance Acoustic Performance Testing

UNCLASSIFIED

Security Classification

AFAPL.TR-70-80

PERFORMANCE AND ACOUSTIC TESTING OF A VARIABLE CAMBER PROPELLER

DONALD P. McERLEAN, 1ST LIEUTENANT. USAF DONALD E. EDWARDS

This document has been approved for public release and tale; its distribution is unlimited.

AFAPL-TR-70-80

FOREWORD

This report summarizes the variable camber propeller test program work

accomplished during the period from March 1970 through July 1970 under

Project 3066, Task 306612, "Propeller Technology," Lt McErlean, AFAPL/TBC,

project engineer. This report was submitted by the authors November 1970.

In-house technical support for the test program and report preparation was

provided by members of the Components Branch, Turbine Engine Division of the

Air Force Aero Propulsion Laboratory. The performance testing was conducted

by Dr. Donald P. McErlean and, the acoustic testing was conducted by

Mr. Donald E. Edwards. Test facilities were under the direction of

Mr, S. W. Blosser of the Experimental Test Branch, Technical Facilities

Division of the Air Fovce Aero Propulsion Laboratory; Mr. George Medisch of

the same Branch was the Chief of the Propeller Test Crew.

Special appreciation is extended to Mr. M. P. Wannemacher of the

Components Branch, Turbine Engine Division of the Air Force Aero Propulsion

Laboratory for acting as associate investigator during the course of this

program, and to the members of the propeller test crew for their assistance

and cooperation.

Technical support was provided by the manufacturer of the propeller,

Detroit Diesel Allison Division of General Motors Corporation, Indianapolis,

Indiana.

This technical report has been reviewed and is approved.

'ERNEST RNEST CT SIMPSON Director, Turbine Engine Division AF Aero Propulsion Laboratory

ii

AFA PL-TR-70-80

ABSTRACT

This report presents the test results obtained from a series of performance

and acoustic near-field measurements on a propeller fitted with a variable

camber feature. The subject propeller, manufactured by the Detroit Diesel

Allison Division of General Motors under a prior Contributing Engineering

Program Contract, effects a change in camber by deflecting a flap positioned

along the 72% chordal line of each blade.

The tests were conducted on the 10,000 horsepower electric whirl rig

located at Wright-Patterson Air Force Base. In comparison with the same

blade with fixed camber, the variable camber feature increased the static

thrust by approximately 11% with a horsepower input of 3500 SHP at 1020 RPM.

The overall sound pressure level and the l/3 octave band frequency spectra did

not appear to be appreciably influenced by increasing the camber on this

propeller.

These tests represent the only test date available on this unique propeller

configuration which has good potential for V/STOL applications.

iii

AFAPL-TR-70-80

TABLE OF CONTENTS

SECTION PAGE

I INTRODUCTION 1

II TEST AND FACILITIES 2

1. Test Vehicle 2

2. Test Plan 3

a. Test Data Recorded 3

b. Propeller Configurations Tested 3

3. Test Facilities 4

a. Horsepower 4

b. Thrust 5

c. RPM 5

d. Acoustic Data Acquisition System 5

El DATA ANALYSIS AND REDUCTION 7

1. Aerodynamic Data 7

2. Acoustic Data 7

IV TEST RESULTS 9

1. Aerodynamic Performance Results 9

a. Thrust vs RPM 9

b. Horsepower vs RPM 9

c. Cx/Cp vs Cp 9

d. Figure of Merit 9

e. Thrust vs Blade Angle 10

AFAPL-TR-70-80

TABLE OF CONTENTS (CONT)

SECTION

2. Acoustic Data

a. Graphical Frequency Spectra

b. Overall Sound Pressure Level

c. Tabular Frequency Spectra

d. Comparison of Measured Sound Pressure Levels With Predicted Values

V CONCLUSIONS AND RECOMMENDATIONS

1. Conclusions

2. Recommendations

APPENDIX RAW TEST DATA

1. Whirl Rig Performance Data

2. Tabular Frequency Spectra

REFERENCES

PAGE

10

10

11

11

11

12

12

12

51

54

70

90

vi

AFAPL-TR-70-80

ILLUSTRATIONS

FIGURE PAGE

1. End View of Variable Camber Blade 13

2. Variable Camber Propeller Installed on Whirl Rig No. 1 14

3. Blade Flap Actuation Mechanism 15

4. Microphone Positions for Acoustic Data Acquisition System 16

5. Pounds Thrust vs Propeller Speed at Various Blade Angles - Zero Blade Flap Deflection 17

6. Pounds Thrust vs Propeller Speed at Various Blade Angles - Full Blade Flap Deflection 18

7. Horsepower vs Propeller Speed at Various Blade Angles - Zero Blade Flap Deflection 19

8. Horsepower vs Propeller Speed at Various Blade Angles - Full Blade Flap Deflection 20

9. Thrust/Horsepower vs Power Coefficient 21

10. Figure of Merit vs Power Coefficient 22

11. Pounds of Thrust vs Blade Angle at 1000 RPM 23

12. Pounds of Thrust vs Blade Angle at 1020 RPM 24

13-28. Graphical Frequency Spectra 26-41

29-34. Overall Sound Pressure Level Diagrams 44-49

vii

AFAPL-TR-70-80

SYMBOLS

D propeller diameter, ft

.- .. c 100,000 f1,0 b / r \* * f r \ AF activity factor = ^ J -§~(-R-) <» (-^-j 0.2

ß blade angle

r radius along blade, ft

R total blade radius, ft

-i.o 3

CLi integrated design lift coefficient s4 j c^j (-5-) *• ("^~')

C^j blade section design lift coefficient

M tip Mach number = -~r^— 60 a N propeller speed, RPM

a speed of sound, ft/sec

a- density ratio, P / P0

p local density, lb-sec2/ft4

PQ sea level standard density, lb-sec2/ft4

„„ 4. J J u test horsepower HP corrected rig horsepower 5:—K

Cn power coefficient 5 ^ l0_ HP

N D

CT thrust coefficient —•5I4 X ,0 lh

N,Dc'» F. M. figure of merit = 0. 798 jr^—

Th corrected rig thrust, pounds t rust

Vlll

AFAPL-TR-70-80

SECTION I

INTRODUCTION

A serious problem with the propellers which are currently used for V/STOL

and STOL applications is that the need for high static thrust has caused the blade

to be designed for takeoff conditions and therefore the performance at cruise

speed is hampered. The development of a high speed V/STOL or STOL turbo-

prop requires that the propeller give good performance in both the static and

flight regimes. An excellent way of accomplishing this high performance

throughout the flight envelope is to utilize a propeller which incorporates vari-

able geometry.

Although the above discussion centers around performance, it is recognized

that the planned application of STOL and V/STOL aircraft for short-haul trans-

portation in and around a civilian environment has caused the noise generated by

these aircraft to become of major importance. Therefore, it was decided that,

to evaluate the performance of propellers for this type of aircraft, it would be

necessary to measure not only thrust, horsepower, and RPM but also the near-

field acoustic signature.

This report presents the results of the performance testing of a variable

camber propeller manufactured by the Detroit Diesel Allison Division of

General Motors. This propeller incorporates a flap, similar to the aileron of a

wing, located along the trailing edge of each blade. When activated, this flap

effectively changes the camber of the blade.

In view of the current interest in improving STOL and V/STOL aircraft

performance and in the noise pollution aspects of such aircraft, the findings of

this report are believed to be of significant value. They represent the only test

data available on this unique propulsor configuration and, hopefully, may provide

a basis for further research into the area of variable geometry propellers.

AFAPL-TR-70-80

SECTION II

TEST AND FACILITIES

1. TEST VEHICLE

The tests described in this report were performed on a variable camber

propeller developed by the Detroit Diesel Allison Division of General Motors.

This propeller, which is basically a standard Aeroproducts A6441FN-606

(Lockheed Electra) blade, was modified by the addition of a flap positioned along

the 72% chordal line of each blade. This flap, similar to the aileron of a wing,

effectively changes the camber of the blade when deflected. This can be seen

quite clearly in Figures 1 and 2.

The blaue flap actuation mechanism, which can be seen in Figure 3, is

brsically a two-position cam which deflects the flap after the blade has

progressed through a specified blade angle. This mechanism operates in the

following manner: When the blades are moved into the takeoff position, the cam

rotates the flap toward the blade thrust face to produce the high camber required

for maximum takeoff thrust. As the blade angle is increased into the cruise

range, the flap moves to its low camber position where it completes the design

airfoil section for high cruise efficiency.

The present configuration deflects the flap at all blade angles of 40° or less.

However, this mechanism was modified slightly for this experiment in order to

allow the flap angle to be varied independently of the blade angle so that a base

line could be drawn for performance/acoustic measurements.

The following are the major characteristics of the propeller:

Diameter 13 feet, 6 inches

Activity Factor 177

Design RPM 1020

Takeoff Horsepower 4200

Integrated Design Lift Coefficient 0. 25

AFAPL-TR-70-80

Equivalent Design Lift Coefficient (Flap Deflected)

Number of Blades

Mater ir. I

0.75

4

SAE 4350 steel, hollow-ribbed construction

2. TEST PLAN

The tests described in this report are standard whirl rig calibration tests

during which both performance and acoustic near-field data were obtained.

a. Test Data Recorded

The following data were recorded, where applicable, through the total

RPM range of the test:

Test Run Number

Time of Day

Total Test Time

Blade Angle, Degrees

Propeller Speed, RPM

Barometric Pressure

Ambient Temperature

Corrected Horsepower

Corrected Thrust

Acoustic Near-Field Signature

b. Propeller Configurations Tested

The following test runs were made with both zero and full-blade flap

deflection:

+25° blade angle, 500 to 1000 RPM in 100 RPM increments plus 1020 and 1050 RPM

*+32.20 blade angle, 500 to 1000 RPM in 100 RPM increments plus 1020 and 1050 RPM

♦+39.2° blade angle, 500 to 1000 RPM in 100 RPM increments plus 1020 and 1050 RPM

AFAPL-TR-70-80

*-H42.80 blade angle, 500 to 1000 RPM in 100 RPM increments plus 1020 and 1050 RPM.

+50.1° blade angle, 500 to 1000 RPM in 100 RPM increments plus 1020 and 1050 RPM.

♦Acoustic near-tield signature was recorded for these configurations.

All blade and flap angles were measured at the 42-inch blade station and

4200 SHP and 1050 RPM were employed as operating limits.

For all the configurations tested, full blade flap deflection consisted of

moving the blade flap 5.4° in the increasing camber direction from the design

airfoil position. The measurement of both blade and flap angle was accom-

plished by using a protractor and a special template designed according to the

manufacturer's blade drawings.

3. TEST FACILITIES

All testing described in this report was done on the 10,000 horsepower

electric whirl rig No. 1 located at Wright-Patterson AFB. In general, this rig

consists of a large concrete pier which houses the electric drive motor, thrust

and RPM measuring equipment, and various accessory drives. The pier rises

about 25 feet off the floor of a large open building. The control room is located

under the pier and the propeller may be observed via a periscope and strobe

light arrangement. The following paragraphs give a brief description of the

horsepower, thrust, and RPM measuring systems.

a. Horsepower

The input power to the propeller is calculated from measuring the armature

voltage and amperage at the electric drive motor. Predetermined correction

factors are then applied to allow for the copper and field winding losses. The

resultant watts are then converted to horsepower and an atmospheric correction

factor is used to adjust the data to standard day conditions. These calculations

are made with an electronic desk calculator during the course of the test so

that field curves can be drawn to check for obvious data discrepancies.

AFAPL-TR-70-80

The system is calibrated against a well documented test propeller whose blades

have been accurately set and locked into place. No load losses are determined

by motoring the rig at various RPM settings.

b. Thrust

The thrust is measured by converting the movement of the propeller shaft

to hydraulic pressure via a hydraulic diaphragm. The pressure signal is then

directly converted to pounds thrust with a precalibrated Emery-Täte load indi-

cator and then corrected to standard day conditions. The thrust system is

calibrated statically by applying a known load (lead weights) to the propeller

shaft.

c. RPM

Accurate shaft RPM was obtained from a magnetic pickup which receives

impulses from the drive motor shaft. These impulses are then presented on a

digital display in the control room as propeller RPM.

d. Acoustic Data Acquisition System

The acoustic data acquisition system consisted of six channels. Each

channel employed a one-half inch Bruel and Kjaer microphone and cathode

follower. The microphones were clamped to microphone stands which gave them

the same elevation as the propeller hub and were positioned as shown in

Figure 4. A preamplifier was used to drive the signal through 250 feet of four-

conductor shielded cable. The cable connected the microphone assembly to the

instrumentation in the control room where the signal was monitored by an oscil-

loscope and a Bruel and Kjaer voltmeter which was built into a third-octave

spectrum analyzer. An Ampex FR-1300 tape unit was used to record the signal

and a junction box with variable attenuators was used for system calibration.

Power supplies for the microphones and amplifiers were also located in the

control room.

AFAPL-TR-70-80

A complete list of the data acquisition system instrumentation follows:

Microphone - half-inch Bruel and Kjaer condenser type 4133

Cathode Follower - Bruel and Kjaer type 2619

Preamplifier - general purpose line drive amplifier, Fairchild ADO-24

Cable - 20 gage, 4-conductor, shielded

Tape Recorder - Ampex FR1300, 30 IPS, extended mode,

54 KHz center frequency

6

AFAPL-TR-70-80

SECTION m

DATA ANALYSIS AND REDUCTION

1. AERODYNAMIC DATA

As was previously stated, the performance data was taken directly from the

Instrumentation in the control room. This data is then corrected for the various

loss and atmospheric effects by employing predetermined correction factors.

The data in this form is then delivered to the Project Engineer for reduction.

This is accomplished by using a computer program written for the IBM 7094

Digital Computer at Wright-Patterson Air Force Base. This program is entitled

"Computer Program for Reducing Static Propeller Test Data" and is contained

in Reference 1. The explanation of the program contained here generally follows

that of Chopin (Reference 2).

The program accepts whirl rig test data in precisely the format in which it

is taken from the rig by the test crew. This is then reduced by the computer

into power coefficient (Cp), thrust coefficient (C-p), Cx/Cp, figure of merit

(F. M.), thrust/horsepower (Th/HP), and propeller tip Mach number.

The computer then fits a second-degree polynomial, employing the method

of least squares, through six consecutive test data points which are distributed

on either side of a selected tip Mach number value. This routine continues until

smoothed horsepower and thrust curves are created for the entire range of tip

Mach numbers. The reduced data is then presented in two forms: coefficients

computed from the raw test data, and coefficients computed from the fitted curves

at preselected tip Mach number increments.

For this series of tests, a tip Mach number increment of 0.025 from

M - 0.300 to the last data point was employed. The computer printouts of the

reduced data are contained in the Appendix.

2. ACOUSTIC DATA

The acoustic data, which was recorded on magnetic tape, was reduced by

utilizing the data analysis capability of the Air Force Flight Dynamics

Laboratory, Wright-Patters on AFB, Ohio.

A FA PL-TR-70-80

The magnetic recording tape was run on a Honeywell 7600 tape transport from which the signal was analyzed by a General Radio, type 1921, third-octave, real-time, spectrum analyzer. The frequency spectra from the analyzer were then printed in tabular form on paper tape.

Selected frequency spectra were then programmed into an IBM 1800 computer for graphical presentation by a Calcomp plotter. The spectrum analyzer center

frequencies and filter numbers are shown in the tabular acoustic data contained in the Appendix.

"

A FA PL-TR-70-80

SECTION IV

TEST RESULTS

1. AERODYNAMIC PERFORMANCE RESULTS

a. Thrust vs RPM

Figures 5 and 6 show the thrust generated by the propeller at various blade

angles with increasing RPM. Comparison of the curve for the zero flap angle

blade with the curve for the flap-deflected blade shows a much more marked

drop in thrust for the flap-deflected case when the blade angle is increased past

the stall point. This behavior is not unusual as it exhibits the basic difference

between the effective camber of the two blades.

b. Horsepower vs RPM

Figures 7 and 8 display the increase in the power absorbed by the propeller

at various blade angles with increasing RPM. Comparison of the two curves

shows that, at each blade angle-RPM combination, the blade absorbed (or

required) more horsepower with the flap deflected than it did without the flap

deflected.

c. Cx/Cp vs Cp

Figure 9 is essentially a curve of thrust/horsepower at various power

settings. As can be seen from the figure, the effect of RPM (as reflected in

tip Mach number) was negligible, except at low power settings. What was most

interesting was the fact that the curve for the high cambered blade (flap deflected)

was always above the curve for the low cambered blade. Thus, the blade with

the flap deflected always has the advantage in thrust production per horsepower,

although this advantage is slight at high power coefficients.

d. Figure of Merit

The Figure of Merit is essentially a measure of the static efficiency of a

propeller or helicopter rotor. Figure 10 shows that the deflection of the blade

9

AFAPL-TR-70-80

flap caused an average increase in the Figure of Merit of approximately 5 points.

It is also interesting to note that again there was only a very slight effect due to

changing the propeller speed at a fixed blade angle.

e. Thrust vs Blade Angle

Probably the most significant conclusions can be drawn from Figures 11

and 12. These figures illustrate the variation in thrust with blade angle for a

given propeller RPM. Also shown on these plots are some representative cross-

plot lines of constant horsepower. Therefore, assuming a constant speed

propeller (which is the actual operational design of the tested configuration) and

a horsepower which is fixed by the turbo machinery involved, these curves show

the actual gain in static thrust due to the variable camber feature.

Figure 12, at 1020 RPM, showed that the increase in the blade camber

caused by deflecting the flap resulted in about an 11% thrust increase at the

3500 SHP level and about a 7% increase at the 4200 SHP level.

It should be noted, however, that it was not possible to determine from the

data whether this was an optimum configuration. A much more extensive test

program would have to be carried out to study the effects of flap chord, de-

flection angle, basic blade shape, etc. Testing of this scope was simply not

possible within the confines of the present effort.

2. ACOUSTIC DATA

The microphone positions utilized to obtain the acoustic data are shown in

Figure 4.

a. Graphical Frequency Spectra

Selected frequency spectra as plotted by the Calcomp plotter are illustrated

in Figures 13 through 28. The values selected are representative of a high and

low blade angle both with and without the flap deflected.

10

AFAPL-TR-70-80

An interesting observation which may be obtained from the graphical

spectra of microphone positions 5 and 6 is that the broadband vortex noise

propagated forward from the plane of rotation does not seem to be affected by

the deflection of the blade flap.

b. Overall Sound Pressure Level

Figures 29 through 34 present the overall sound pressure level for each

microphone position at three selected RPM values for each configuration

tested. Except for microphone position 4, which is along the axis of expected

maximum sound pressure level, the flap caused no consistent increase in sound

pressure level.

c. Tabular Frequency Spectra

Included in the Appendix with the performance data are tables of the

measured sound pressure level for each center frequency in the 1/3 octave

band analysis. This data may then be plotted to obtain graphs similar to

Figure 13 for any propeller test configuration desired.

d. Comparison of Measured Sound Pressure Levels With Predicted Values

A detailed comparison of the measured near-field noise levels with existing

prediction methods (Reference 3) has indicated maximum deviations of +13 db

and -7 db. The average deviation between measured and predicted data is +5 db

to -3 db. Inaccuracies in the prediction methods do not fully account for the

discrepancies between measured and predicted data. Additional studies are

currently under way to determine the acoustic characteristics of the whirl rig

facility in detail. The effect of reverberation on the accuracy of measured near-

field data will be investigated.

11

AFAPL-TR-70-80

SECTION V

CONCLUSIONS AND RECOMMENDATIONS

1. CONCLUSIONS

The variable camber propeller with blade flaps deflected showed approxi-

mately 11% gain in static thrust at 3500 SHP and 1020 RPM. This is reflected in

a gain of 1-1/2 to 3 points in the Figure of Merit at all power coefficients

tested.

The overall sound pressure level was practically unaffected by deflecting

the blade flaps. This result was somewhat unexpected, especially for the

broadband vortex noise.

2. RECOMMENDATIONS

The manufacturer of the propeller felt that a 10° flap angle should have been

the maximum deflection angle. However, despite repeated attempts on the rig

and in the assembly shop, only an 8° deflection angle was obtained and of that

only 5.4° was in the positive (increasing camber) direction. Therefore, one

recommendation would be to take the present configuration and, with some

delicate machining, attempt to obtain the 10° deflection angle.

Additionally, since this concept has certainly shown that it is feasible,

further work is warranted to try and optimize the flapped blade configuration.

Hopefully, different variable geometry concepts will be tested on a con-

tinuing basis and will allow direct comparison of the results for each

configuration. Since the static thrust of V/STOL machines has been considered

a high risk area of V/STOL propulsion, this work should have considerable

application.

12

AFAPL-TR-70-80

Figure 1. End View of Variable Camber Blade

AFAPL-TR-70-80

Figure 2. Variable Camber Propel ler Installed on Whirl Rig No. 1

14

AFAPL-TR-70-80

AFAPL-TR-70-80

20

OS

1 11

O 5

I 2 O O

D/4 I- ■D/2

0 * Prope Her Diameter

3

O

4 o

Figure 4. Microphone Positions for Acoustic Data Acquisition System

16

AFAPL-TR-70-80

8000

7000

6000

50 00

5 4000

3000

2000

1000

500 600 700 800 900 Revolutions per Minute ( RPM )

1000

Figure 5. Pounds Thrust vs Propeller Speed at Various Blade Angles - Zero Blade Flap Deflection

17

AFAPL-TR-70-80

9000

8000

7000

6000

5000

4000

3000

2000

1000

)3 =39.2^ Z3

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500 600 700 800 900 Revolutions per Minute (RPM)

1000

Figure 6. Pounds Thrust vs Propeller Speed at Various Blade Angles - Full Blade Flap Deflection

18

AFAI-L-TR-TO-SO

4000

3000

a. x

a> » o a. • 2000 w o I

1000

I

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NO FLAP

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500

Figure 7.

600 1000 700 800 900 Revolutions per Minute ( RPM )

Horsepower Vo Propeller Speed at Various Blade Angles - Zero Blade Flap Deflection

19

AFAPL-TR-70-80

4000

500

Figure 8.

600 1000 700 800 900 Revolutions per Minute (RPM)

Horsepower vs Propeller Speed at Various Blade Angles - Full Blade Flap Deflection

20

AFAPL-TR-70- 80

Figure 9. Thrust/Horsepow, er va Power Coefficient

21

AFAPL-TR-70-80

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A FA PL-TR-70-80

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Figure 11. Pounds of Thrust vs Blade Angle at 1000 RPM

23

AFAPL-TR-70-80

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8000

7500

7000

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6500

6000

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50

Figure 12. Pounds of Thrust vs Blade Angle at 1020 RPM

24

AFAPL-TR-70-80

GRAPHICAL FREQUENCY SPECTRA

Figures 13 through 28

25

A FA PL-TR-70-80

150

X/0 = 0 0 Y/D - 00

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120

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Mike Position 2 BLADE

RPM HP ANGLE X 900 257 32.0 A 700 726 320 VI000 2224 32.0

FLAP ANGLE « 0°

50 II I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I

ONE-THIRD OCTAVE BAND CENTER FREQUENCY IN HZ

Figure 13

26

AFAPL-TR-70-80

150

Mike Position

X/D = 0 O Y/D « 0-0

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ONE-THIRD OCTAVE BAND CENTER FREQUENCY IN HZ

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AFAPL-TR-70-80

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ISO

140

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AFAPL-TR-70-80

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ONE-THIRD OCTAVE BAND CENTER FREQUENCr IN HZ

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AFAPL-TR-70-80

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ONE-THIRD OCTAVE BAND CENTER FREQUENCr IN HZ

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AFAPL-TR-70-80

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ONE-THIRD OCTAVE BAND CENTER FREQUENCY IN HZ

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AFAPL-TR-70-80

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34

AFAPL-TR-70-80 ISO

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35

AFAPL-TR-70-80

150

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AFAPL-TR-70-80

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37

AFAPL-TR-70-80

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38

AFAPL-TR-70-80

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AFAPL-TR-70-80

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Figure 28

41

AFAPL-TR-70-80

BLADE ANGLE « 32.2

FLAP ANGLE = 0.0

6

O Overall Sound Pressure Level . db*

98 106 I 18

RPM

500 700

1000

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I 2

o o 3

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Level, db

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98 107 121

RPM

500 700

1000

Overa II Sound Pressure

4 Level, db

o 99 106 120

RPM

500 700

1000

Figure 29

44

AFAPL-TR-70-80

BLADE ANGLE =32.2

FLAP ANGLE = 5.0

6

o Overall Sound Pressure Level , db* RPM

99 500 108 700 118 1000

\

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103 500 112 700 122 tooo

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Level, db RPM

105 102 115 112 128 127

98 108 121

500 700

1000

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Overall Sound Pressure

4 Level, db 0 99

108 120

RPM

500 700

1000

Figure 30

45

AFAPL-TR-70-80

BLADE ANGLE =39.2

FLAP ANGLE =0.0

6

O Overall Sound Pressure

Level, db* RPM

103 500 Ml 700 122 1000

o Overall Sound Pressure

Level, db

106 116 126

RPM

500 700

1000

1 2 3

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Level, db RPM

110 108 103 500 121 119 113 700 127 128 123 1000

*decibel reference 0.0002 microbar

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4 Level.^Ib

o RPM

103 I 13 122

500 700

1000

Figure 31

46

AFAPL-TR-70-80

BLADE ANGLE =39.2

FLAP ANGLE : 5.0

6

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Level, db*

102 112 123

RPM

500 700

1000

O Overall Sound Pressure

Level, db

107 117 126

RPM

500 700

1000

1 2 3

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Level , db RPM

110 109 104 500 122 120 114 700 127 127 124 1000

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4 Level, db

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1000

Figure 32

47

AFAPL-TR-70-80

BLAUE ANGLE =42.8 FLAP ANGLE = O. 0

o Overall Sound Pressure

Level, db*

105 115 124

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1000

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Level, db RPM

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120 700 127 1000

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Level, db RPM

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106 117 124

500 700

1000

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1000

Figure 33

48

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1000

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Level, db

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Figure 34

49

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Figure 34

49

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■ I I Hill WWIIWJII. * 111 iiin>i»iiJin<iniil|p)li|MIHWUHWHinMlllJ -M,,—.....

AFAPL-TR-70-80

APPENDIX

RAW TEST DATA

51

- ■

AFAPL-TR-70-80

COMPUTER PRINTOUT

Line 3

BETA - Test blade angle (reference only)

AF - Blade activity factor (reference only)

DIA - Propeller diameter in feet

NBL - Number of blades in hub (reference only)

TEMPC - Ambient temperature in degrees Centigrade

TEMPR - Ambient temperature in degrees Rankine

SIGMA - Density ratio (reference only)

RAW DATA POINTS * * * * *

RPM - Propeller rpm

HP - Corrected horsepower

TH - Corrected thrust

TMACH - Propeller tip Mach number

RCT - Raw thrust coefficient

RCP - Raw power coefficient

RCT/CP - Ratio of raw thrust to raw power coefficient

RFM - Raw figure of merit

RTH/HP - Ratio of raw corrected thrust to corrected horsepower

52

,—.— -""WW*

I

AFAPL-TR-70-80

FITTED CURVE DATA FOR CONSTANT MACH NUMBER INCREMENTS ♦ ♦ ♦ ♦ ♦

MACH - Selected Mach number increment

HP - Horsepower at Mach increment

TH - Thrust at Mach Increment

TIPS - Propeller tip speed in ft/sec corresponding to Mach increment

RPM - Propeller rpm at Mach increment

CT - Thrust coefficient at Mach increment

CP - Power coefficient at Mach increment

CT/CP - Ratio of thrust coefficient to power coefficient at Mach increment

FM - Figure of merit at Mach increment

TH/HP - Ratio of thrust to horsepower at Mach increment

53

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AFAPL-TR-70-80

2. TABULAR FREQUENCY SPECTRA

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70

AFAPL-TR-70-80

Blodt Angle 32» Flop Angle 0° RFM_500_

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71

AFAPL-TR-70-80

Blade Angle 32°

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10 25.0 077 076 069 067 067 063

9 20.0 069 067 064 062 064 060

8 16.0 067 065 063 061 061 060

7 12.5 071 065 060 060 060 060

6 10.0 064 061 060 060 060 060

5 8.0 060 062 060 060 OCO 060

4 6.3 060 060 060 060 060 060

3 5.0 060 0G0 060 060 060 060

2 4.0 060 060 060 060 060 060

1 3.15 060 061 060 060 060 060

♦Decibel reference .0002 microbar

72

■••

AFAPL-TR-70-80

Bladf Angle g*?0

FIOD Anolt 0°

RPM 1000

Filter Number

Center Frequency

Microphone Numbers J

1 2 3 4 5 6 M,

db* db db db db db

40 Overall 126 126 121 120 121 118

39 20,000. 080 080 080 080 080 080

38 16,000. 087 083 082 080 086 082

37 12,500. 099 094 094 090 097 098

36 10,000. 106 101 102 098 105 100

35 8,000. 106 104 103 100 106 102

34 6,300. 107 103 104 101 107 102

33 5,000. 108 104 105 103 108 104

32 4,000. 109 105 106 103 108 104

31 3,150. 109 105 106 105 108 105

30 2,500. 109 105 106 104 108 105

29 2,000. 109 105 106 105 108 105

28 1,600. 109 106 107 106 108 105

27 1,250. 110 106 107 107 109 105

26 1,000. 111 107 108 106 109 105

25 800. 110 106 109 106 109 105

24 630. 110 108 108 107 110 105

23 500.0 109 106 108 109 111 106

22 400.0 108 107 108 110 111 108

21 315.0 108 106 104 105 113 107

20 250.0 108 109 107 10Ö 110 105

19 200.0 110 111 104 105 111 106

18 160.0 106 103 106 099 102 098

17 125.0 118 114 118 108 109 106

16 100.0 097 098 096 092 096 091

15 80.0 112 113 099 104 096 097

14 63.0 125 126 m 117 107 110

13 50.0 101 10^ 090 093 087 086

12 40.0 090 090 082 082 081 080

11 31.5 088 087 08^; 081 080 080

10 25.0 086 086 080 080 080 080

9 20.0 084 083 080 080 080 080

8 16.0 087 083 080 080 080 080

7 12.5 083 081 080 080 080 080

6 10.0 081 080 080 080 080 080

5 8.0 080 080 080 080 080 080'

4 6.3 080 080 080 080 080 080

3 5.0 080 080 080 080 080 080

2 4.C 080 080 080 080 080 080

1 3.15 080 080 080 080 082 080

♦Decibel reference . 0002 microbar

73

"TTW .»IRJI .1 ,JJIII,I»PIIV

AFAPL-TR-70-80

Blöd« Angl« 32(

Flap Anqlt 5° RPM 500

Filt«r Number

Center Frequency

Microphone Numbers I

1 2 3 4 5 6 jb

db* db db db db db

40 Overall 105 102 099 099 103 099 39 20.000. 060 060 060 060 060 060 38 16.000. 067 063 061 060 064 060 37 12.500. 078 075 073 069 076 072 36 10.000. 085 082 080 077 083 079 35 8,000. 087 084 081 079 085 081 34 6.300. 088 085 083 081 086 082 33 5,000. 089 087 085 082 087 083 32 4.000. 090 088 086 084 088 085 31 3.150. 092 089 087 086 090 086 30 2.500. 092 090 087 086 090 087 29 2,000. 092 089 088 086 090 087 28 1.600. 092 090 088 087 090 086 27 1.250. 092 090 088 087 090 086 26 1.000. 092 089 088 087 089 086 25 800. 092 090 088 088 089 086 24 630. 093 091 088 088 090 087 23 500.0 092 090 088 089 091 088 22 400.0 091 091 089 091 093 089 21 315.0 081 091 086 089 094 088 20 250.0 092 090 089 088 093 088 19 200.0 090 088 086 088 094 091 18 160.0 087 088 084 088 091 085 17 125.0 085 086 086 084 091 082 16 100.0 081 086 080 083 086 079 15 80.0 081 078 073 074 080 073 14 63.0 090 083 076 083 089 080 13 50.0 075 076 070 068 072 067 12 40.0 088 083 073 070 074 066 11 31.5 100 095 083 080 083 073 10 25.0 076 071 063 061 066 060 9 20.0 064 062 060 060 061 060 8 16.0 067 064 061 060 063 061 7 12.5 063 063 062 060 062 061 6 10.0 060 060 060 060 060 060 5 8.0 061 060 060 060 060 060 4 6.3 060 060 060 060 060 060 3 5.0 060 060 060 060 060 060 2 4.0 060 060 060 060 060 060 1 3.15 060 060 060 060 060 060

♦Decibel reference .0002 microbar

74

»■ w»wml.,<,mm»m*»»i>m' ; ■■■— '■'■■'"■■ -

-"™™~

AFAPL-TR-70-80

Blodt Angle Flop Angle RPM 700 '

32l

5°

Filter Number

Center Frequency

1 Microphone Number •

1 2 3 4 5 6 ib

db* db db db db db

40 Overall 115 112 108 108 111 108 39 20,000. 065 062 060 060 063 060 38 16,000. 077 073 070 067 075 070 37 12,500. 089 086 084 080 087 082 36 10,000. 096 093 091 088 094 090 35 8,000. 097 095 093 090 096 092 34 6,300. 098 096 094 092 097 093 33 5,000. 100 098 095 093 098 094 32 4.000. 101 098 096 094 099 095 31 3,150. 102 099 097 096 100 097 30 2,500. 102 100 097 095 099 096 29 2,000. 102 100 097 096 099 096 28 1.600. 102 099 097 096 099 095 27 1,250. 102 099 097 096 099 095 26 1,000. 102 099 097 097 099 098 25 800. 102 099 098 097 099 095 24 630. 102 101 098 098 100 096 23 500.0 101 100 098 099 100 096 22 400.0 101 100 097 100 101 097 21 315.0 100 099 094 099 102 096 20 250.0 099 097 096 097 102 096 19 200.0 097 095 092 093 100 095 18 160.0 094 093 091 092 096 090 17 125.0 095 093 092 092 095 088 16 100.0 102 099 088 093 097 090 15 80.0 092 090 082 083 088 083 14 63.0 036 086 077 077 082 076 13 50.0 111 106 089 093 094 084 12 40.0 101 097 081 084 085 075 11 31.5 080 077 073 071 073 065 10 25.0 079 077 070 068 071 065 9 20.0 075 071 063 063 066 060 8 16.0 072 071 067 065 066 061 7 12.5 071 070 063 063 065 063 6 10.0 069 066 060 061 061 060 5 8.0 064 062 060 060 060 060 4 6.3 063 063 060 061 060 060 3 5.0 062 060 060 061 060 060 2 4.0 060 060 060 060 060 060 1 3.15

j

060 060 060 060 060 060

♦Decibel reference . 0002 microbar

75

AFAPL-TR-70-80

Blodc Angle 3^

Flop AllgIt 5° RPM mon

oO

Filter Number

Center Frequency

' Microphone Numbers 1

1 2 3 4 5 6 Jfc>

db* db db db db db

40 Overall 128 126 121 120 121 118 39 20,000. 080 080 080 080 080 080 38 16,000. 087 083 083 080 087 082 37 12,500. 098 093 096 091 096 094 36 10,000. 106 100 102 099 105 100 35 8,000. 107 101 104 101 107 102 34 6,300. 107 102 105 102 107 108 33 5,000. 109 103 106 103 109 105 32 4,000. 109 104 106 104 109 105 31 3,150. 109 104 107 105 109 105 30 2,500. 109 104 106 105 109 105 29 2,000. 109 105 107 105 109 105

28 1,600. 109 105 107 105 108 105

27 1,250. 110 105 108 107 109 106

26 1,000. 110 106 108 106 109 105

25 800. 110 106 108 107 109 105

24 630. 111 107 109 107 109 105

23 500.0 112 105 109 109 110 106

22 400.0 113 105 108 108 109 105

21 315.0 113 106 104 106 110 106

20 250.0 113 109 106 105 108 105

19 200.0 113 112 103 101 111 105

18 160.0 109 107 104 100 103 098

17 125.0 120 119 116 105 111 101 16 100.0 105 101 096 093 096 091 15 80.0 113 113 100 104 098 099 14 63.0 126 126 114 117 111 111 13 50.0 105 102 091 093 090 088 12 40.0 101 092 083 083 081 080

11 31.5 099 090 081 082 080 080 10 25.0 099 087 080 080 080 080

9 20.0 098 084 080 080 080 080

8 16.0 098 082 080 080 080 080 7 12.5 096 080 080 080 080 080

6 10.0 094 080 080 080 080 080

5 8.0 093 080 080 080 080 080

4 6.3 092 080 080 080 080 080

3 5.0 091 080 080 080 080 080

2 4.0 090 080 080 080 080 080

1 3.15 088 080 080 080 080 080

♦Decibel reference .0002 microbar

76

iip!WlWlP)".^^-Mfm.«IIWiPHW?,"ll|^!L "

AFAPL-TR-70-80

Blodt AngU 390

Plop Angl« o0

RPM 500

♦Decibel reference .0002 microbar

77

■

AFAPL-TR-70-80

Blöd« Anqlt 39°

Flop Ang!« RPM 700

tiO

Fllttr Number

Centtr Frequency

Microphone Number« I 1 2 3 4 5 6

db* db db db db db

40 Overall 121 118 113 113 116 111 39 20.000. 080 080 060 060 063 060 38 16.000. 080 080 068 066 075 069 37 12.500. 088 087 083 078 088 082 36 10.000. 095 094 091 087 095 089 35 8.000. 097 096 092 090 097 092 34 6.300. 098 097 094 091 098 093 33 5,000. 100 099 096 093 099 095 32 4.000. 100 100 096 094 100 096 31 3,150. 101 101 097 096 101 097 30 2.500. 102 102 098 096 101 097 29 2.000. 102 102 099 097 102 098 28 1.600. 103 102 100 099 102 098 27 1.250. 104 104 101 100 103 099 26 1,000. 105 105 102 101 103 099 25 800. 105 105 103 102 104 101 24 630. 108 107 104 104 105 101 23 500.0 106 106 104 105 106 102 22 400.0 106 107 104 104 107 103 21 315.0 107 107 102 103 107 101 20 250.0 106 105 104 102 107 102 19 200.0 103 102 098 100 106 101 18 160.0 101 102 099 099 102 097 17 125.0 103 102 101 098 100 095 16 100.0 108 106 094 094 097 095 15 80.0 101 100 092 092 098 094 14 63.0 096 095 084 084 089 084 13 50.0 119 115 094 092 099 087 12 40.0 109 106 086 085 091 082 11 31.5 089 086 078 075 077 072 10 25.0 086 083 071 070 072 067 9 20.0 080 080 068 068 068 062 8 16.0 080 080 065 064 063 060 7 12.5 080 080 065 065 062 060 6 10.0 081 080 064 062 060 060 5 8.0 080 080 061 064 060 060 4 6.3 080 080 060 065 060 060 3 5.0 080 080 060 064 060 060 2 4.0 080 080 Ü6Ö 062 060 060 1 3.15 080 080 065 062 060 060

♦Decibel reference .0002 microbar

78

- iillJWIIUl1!

■ -'WMW""""'."" '

AFAPL-TR-70-80

Bladt Angle a9< Flop Angle 0°

Filter Number

Center Frequency

Microphone Numbers 1 2 3 4 5 6

jk db* db db db db db

40 Overall 127 127 123 122 126 122 39 20.000. 080 080 080 080 080 080 38 16,000. 083 083 082 081 087 083 37 12,500. 094 094 092 091 099 095 36 10,000. 101 101 100 090 106 101 35 8,000. 103 101 102 100 108 104 34 6,300. 104 103 103 101 109 105 33 5,000. 104 104 104 103 110 106 32 4.000. 105 105 105 104 110 107 31 3,150. 106 106 106 105 111 107 30 2.500. 107 107 107 105 111 108 29 2,000. 107 107 107 106 112 108 28 1,600. 108 108 108 107 112 108 27 1.250. 109 109 109 109 113 109 26 1.000. 109 109 109 109 114 110 25 800. 109 110 110 110 114 110 24 630. 110 111 111 111 115 111 23 500.0 110 111 111 111 115 110 22 400.0 111 111 112 110 116 111 21 315.0 111 110 no 108 115 110 20 250.0 112 112 111 107 114 110 19 200.0 110 112 108 109 114 110 18 160.0 110 110 109 106 111 106 17 125.0 120 118 118 107 115 110 16 100.0 105 105 103 102 107 102 15 80.0 112 113 105 106 102 103 14 63.0 125 126 117 119 112 115 13 50.0 102 103 099 099 097 094 12 40.0 096 096 097 095 094 085 11 31.5 093 094 093 090 093 081 10 25.0 090 092 092 089 089 080 9 20.0 089 088 088 088 089 080 8 16.0 084 085 087 086 088 080 7 12.5 084 083 082 083 087 080 6 10.0 083 082 082 081 087 080 5 8.0 08 T 080 080 080 083 080 4 6.3 080 080 080 080 083 080 3 5.0 080 080 080 080 080 080 2 4.0 080 080 080 080 080 080 1 3.15 082 080 080 080 080 080

♦Decibel reference .0002 microbar

79

-

^MtTWTB^yullUiyiWHW'IIUIIIWIJ -" "T"" iii,Hi|ill|ii|ii|i|.|.HllHl"|l'l'-"lJ<l"

AFAPL-TR-70-80

Blodt Anglt 39°

Flop AnoU 5° RPM 500

FilUr Numbtr

Center Frtquency

Microphone Numbers |

1 2 3 4 5 6

db* db db db db db

40 Overall 110 109 104 103 107 102 39 20.000. 060 060 060 060 060 060 38 16.000. 064 064 060 060 065 060 37 12.500. 077 077 072 069 076 071 36 10,000. 084 084 080 077 084 079 35 8.000. 087 086 082 079 086 081 34 6.300. 088 088 084 081 087 082 33 5.000. 090 090 085 082 089 084 32 4.000. 091 090 086 083 089 085 31 3.150. 092 092 088 085 091 086 30 2.500. 092 092 088 086 090 086 29 2.000. 093 092 088 087 091 087 28 1.600. 094 093 089 088 092 087 27 1.250. 095 094 090 089 092 088 26 1,000. 096 095 091 091 093 088 25 800. 096 096 093 092 094 090 24 630. 098 098 094 094 095 091 23 500.0 096 097 095 095 097 093 22 400.0 099 100 096 096 099 094 21 315.0 098 099 092 095 099 094 20 250.0 098 098 095 094 099 094 19 200.0 095 096 092 092 098 094 18 160.0 093 095 092 092 095 091 17 125.0 093 093 092 090 092 087 16 100.0 091 092 086 085 091 085 15 80.0 090 088 083 082 087 083 14 63.0 097 091 082 081 086 082 13 50.0 086 087 079 080 082 079 12 40.0 095 091 078 075 079 075

11 31.5 107 103 088 082 039 084 10 25.0 083 079 068 068 070 067

9 20.0 072 069 063 060 064 060 8 16.0 073 071 064 062 061 060 7 12.5 070 066 060 061 060 060 6 10.0 067 065 062 062 060 060 5 8.0 068 063 060 060 060 060 4 6.3 064 062 060 060 060 060 3 5.0 061 060 060 060 060 060 2 4.0 063 060 060 060 060 060 1 3.15 060 060 060 060 060 060

♦Decibel reference .0002 microbar

80

mwewtr1

AFAPL-TR-70-80

Blodt Awglt 39c

flap Anglt ö0

RPM 700~

Filter Number

Center Frequency

Microphone Numbers 1 2 3 4 5 6

M, db* db db db db db

40 Overall 122 120 113 113 117 112 39 20,000. 080 080 060 061 064 060 38 16,000. 080 080 069 069 075 070 37 12,500. 088 087 083 079 088 083 36 10,000. 095 094 091 087 096 090 35 8,000. 097 096 093 090 097 092 34 6,300. 099 098 095 092 099 094 33 5,000. 100 100 096 094 100 095 32 4,000. 100 101 097 095 101 096 31 3,150. 102 101 098 096 102 097 30 2,500. 102 102 099 097 101 097 29 2,000. 102 103 099 098 102 098 28 1,600. 103 104 101 099 10a 098 27 1,250. 104 104 101 101 103 099 26 1,000. 106 105 102 102 104 099 25 800. 105 106 104 103 105 101 24 630. 107 108 105 105 106 102 23 500.0 106 107 105 106 107 102 22 400.0 108 109 105 106 108 104 21 315.0 108 108 102 105 108 102 20 250.0 106 106 104 103 107 103 19 200.0 103 103 100 100 106 101 18 160.0 101 104 100 100 10A 098 17 125.0 104 104 102 100 100 09(i

16 100.0 109 107 096 094 099 094 15 80.0 102 100 091 094 099 094 14 63.0 098 097 085 084 090 08 r; 13 50.0 120 117 093 094 098 089 12 40.0 111 108 085 088 091 084 11 31.5 091 089 079 078 079 072 10 25.0 087 086 073 07^ 073 067 9 20.0 082 081 069 068 070 061 8 16.0 083 081 069 067 06 Ü 060 7 12.5 084 081 066 064 065 060 6 10.0 080 080 063 067 OC^ 060 5 8.0 080 080 061 067 060 060 4 6.3 080 080 060 067 060 060 3 5.0 080 080 060 066 060 ÜG0 2 4.0 080 080 060 063 060 060 1 3.15 080 080 060 060 060 0G0

♦Decibel reference .0002 microbar

81

■

AFAPL-TR-70-80

Blodt Anglt 39° Flop AnoU 5° RPM 1000

♦Decibel reference .0002 microbar

Filter iNumbtr

Ctnttr Frequency

1 Microphone Number« "1 1 2 | 3 4 1 9

6 | Jk

db* db db db db db i 40 Overall 127 127 124 122 128 122 39 20,000. 080 080 080 080 080 080 38 16,000. 084 083 082 082 087 083 37 12.500. 095 093 0GJ 092 099 094 36 10,000. 101 101 100 098 106 101 35 8.000. 103 101 102 100 108 103 34 6,300. 1 105 103 103 101 109 705 33 5,000. i 106 104 105 103 110 106

1 32 4.000. 106 105 105 104 111 107 31 3.150. 107 107 106 105 112 108 30 2.500. 107 106 107 105 HI 108

1 29 2.000. 108 107 107 106 112 109 | 28 1,600. 109 108 108 107 113 108 i 27 1,250. 109 109 109 108 113 109 |

26 1,000. 110 110 110 109 114 110 25 800. 110 110 111 110 114 HI 24 630. 111 111 112 111 115 112 23 500.0 110 110 112 111 115 112 22 400.0 112 112 112 110 115 112 1 21 315.0 112 111 110 109 115 110 | 20 250.0 112 113 110 108 114 no 19 200.0 111 112 110 109 114 109

i 18 160.0 110 109 110 106 110 107 1 17 125.0 119 119 119 107 115 HI } 16 100.0 105 105 104 102 107 102 15 80.0 113 113 105 107 102 104 f

i i4 63.0 126 126 116 120 112 117 ) 13 50.0 102 103 098 098 096 094 1

1 12 40.0 096 096 097 094 094 086 j 11 31.5 094 094 094 091 092 082 10 25.0 091 092 092 087 092 082 9 20.0 087 089 089 086 089 080 8 16.0 088 087 087 085 092 082 7 12.5 083 084 084 083 088 081 6 10.0 081 080 080 080 087 080 |

1 5 8.0 080 081 081 080 085 080

1 4 6.3 080 080 080 080 082 080 1 3 5.0 080 080 080 080 080 080

1 2 4.0 080 080 080 080 080 080 | I 1 3.15 080 080 080 080 080 080

82

wwTWfffVi.^wijnnfPWf-IIIW-""W i WliM-.i i^J^tfHifft(BH ..-^^^„^■I.^^IIII^PUHII.PI" -

AFAPL-TR-70-80

Blodt Anql« 42°

Flop Anglt RPM 500

0°

Filttr Number

Center Frequency

Microphone Numbers |

1 2 3 4 5 6 . M,

db* db db db db db

40 Overall 113 111 106 107 no lOfa 39 20,000. 060 060 060 060 060 060 38 16.000. 064 063 060 060 Obb 060 37 12,500. 077 076 073 070 077 072 36 10.000. 084 083 080 077 08Ü 079 35 8,000. 087 086 082 079 086 082 34 6.300. 088 087 084 081 08 ^ 083 33 5.000. 090 090 086 083 089 084 32 4.000. 091 091 086 084 090 085 31 3.150. 092 092 088 086 091 086 30 2,500. 093 092 088 087 091 087 29 2,000. 093 093 089 088 092 088 28 1,600. 094 094 090 089 092 088 27 1,250. 095 095 091 090 093 089 26 1,000. 096 096 092 092 094 090 25 800. 097 097 095 093 096 091 24 630. 099 100 096 096 097 09Z 23 500.0 099 100 097 098 098 094 22 400.0 102 102 097 099 101 097 21 315.0 103 103 097 099 103 098 20 250.0 103 103 099 099 103 098 19 200.0 101 100 096 097 102 098 18 160.0 099 099 095 096 100 096 17 125.0 096 097 095 093 097 092 16 100.0 096 098 091 088 094 089 15 80.0 096 094 087 088 093 089 14 63.0 098 096 086 086 090 085 13 50.0 092 092 082 084 088 085 12 40.0 097 093 080 078 080 075

11 31.5 108 104 091 083 088 083 10 25.0 086 084 074 071 074 068

9 20.0 078 0V2 OGO 06o 065 060 8 16.0 077 071 063 063 061 OGO 7 12.5 073 069 060 060 062 060 6 10.0 071 068 060 060 060 060 5 8.0 072 068 060 060 060 060 4 6.3 068 069 060 060 060 060

3 5.0 066 067 060 060 060 060

2 4.0 067 063 060 060 060 060

1 3.15 060 064 060 060 060 060

♦Decibel reference .0002 microbar

83

■-..■,-

...,,..•,,• • - -

AFAPL-TR-70-80

Blad« Anql» 42° Flop Anal« 0° RPM 700

Fit tor Number

Center Frequency

Microphone Numbers 1

1 2 3 4 5 6 jk

db* db db db db db

40 Overall 123 121 117 117 120 115 39 20.000. 080 080 061 060 080 060 38 16,000. 080 080 070 069 080 070 37 12,500. 088 088 084 082 088 083 36 10.000. 095 094 091 090 096 090 35 8,000. 097 096 093 091 098 093 34 6,300. 098 098 095 093 099 094 33 5,000. 099 100 096 094 101 096 32 4,000. 101 101 097 096 101 097 31 3,150. 102 102 099 097 102 098 30 2,500. 102 102 099 098 102 098 29 2,000. 103 103 100 099 103 099 28 1,600. 104 104 101 100 103 100 27 1,250. 104 105 102 102 104 100 26 1,000. 106 107 104 104 106 101 25 800. 107 107 106 104 107 103 24 630. 109 110 107 107 108 104 23 500.0 107 110 108 108 109 105 22 400.0 110 112 110 109 111 106 21 315.0 111 112 107 108 112 106 20 250.0 112 111 109 107 111 106 19 200.0 107 108 104 104 111 106 18 160.0 107 108 106 105 107 103 17 125.0 107 108 108 104 105 101

16 100.0 109 108 101 099 103 099 15 80.0 106 106 100 100 106 101

14 63.0 101 100 089 089 097 091

13 50.0 120 117 100 088 102 093

12 40.0 111 107 092 087 095 090

11 31.5 095 090 079 080 081 076

10 25.0 094 087 075 074 080 071

9 20.0 091 085 067 069 080 065

8 16.0 090 084 071 071 080 061

7 12.5 085 084 068 068 080 061

6 10.0 087 084 067 067 080 060 5 8.0 081 080 060 068 080 060 4 6.3 080 080 062 068 080 060 3 5.0 080 080 061 069 080 060 2 4.0 080 080 060 068 080 060 1 3.15 080 080 060 070 080 060

♦Decibel reference .0002 microbar

84

-' ■"■ • " ^ * '

AFAPL-TR-70-Rn

Blöd« Anglt_

nop Angl«_ RPM 992

420

Filttr Numbtr

Ctnttr Frtqutney

Microphone Numbers

1 2 3 4 5 6 Jk

db* db db db db db

40 Overall 127 127 124 124 126 123 39 20,000. 080 080 080 080 080 080 38 16,000. 084 084 082 083 087 083 37 12.500. 096 094 093 094 098 094 36 10,000. 102 101 100 100 106 102 35 8,000. 104 103 102 101 107 103 34 6,300. 104 104 104 103 108 104 33 5,000. 106 105 105 104 109 106 32 4,000. 106 106 105 105 110 106

31 3,150. 107 107 107 106 HI 108 30 2,500. 108 108 107 107 111 108 29 2,000. 109 108 108 108 111 108 28 1,600. 110 109 109 109 113 109 27 1,250. 110 110 no 110 113 110 26 1.000. 111 111 111 111 114 111 25 800. 112 111 112 112 115 112 24 630. 114 113 113 113 116 113 23 500.0 114 113 114 114 116 113 22 400.0 115 114 115 115 118 114 21 315.0 113 113 112 1U 118 113 20 250.0 114 114 113 112 117 114 19 200.0 112 113 111 111 116 112 18 160.0 112 111 113 110 115 112 17 125.0 119 117 116 111 114 112 16 100.0 108 108 106 106 113 109 15 80.0 112 112 105 106 107 104 14 63.0 125 126 117 118 114 117 13 50.0 105 105 099 100 103 098 12 40.0 100 100 098 098 101 092

11 31.5 094 096 092 096 101 090 10 25.0 093 094 091 092 099 090 9 20.0 092 090 088 091 097 088 8 16.0 091 089 089 088 095 089 7 12.5 087 089 084 086 095 085 6 10.0 084 083 080 083 093 081 5 8.0 080 080 080 081 093 080 4 6.3 080 080 080 080 092 080 3 5.0 080 080 080 080 089 080 2 4.0 080 080 080 080 087 080 1 3.15 080 080 080 080 083 080

♦Decibel reference . 0002 microbar

85

AFAPL-TR-70-80

Blodt Anfll«

Flop Angl«, RPM 500 '

420

bo

Filter Number

Center Frequency

Microphone Number l 1 2 3 4 5 6

JL db* db db db db db

40 Overall 113 112 107 108 111 106 39 20.000. 060 060 060 060 060 060 38 16,000. 066 064 061 060 065 061 37 12.500. 078 077 074 071 078 073 36 10,000. 085 084 081 078 085 080 35 8,000. 088 087 083 080 087 082 34 6,300. 089 089 085 082 089 083 33 5,000. 091 090 086 084 090 085 32 4,000. 092 091 088 085 091 086 31 3,150. 093 092 089 087 092 088 30 2,500. 093 093 089 087 092 088 29 2,000. 095 094 090 089 093 088 28 1,600. 095 094 091 090 093 088 27 1,250. 096 095 092 092 094 089 26 1,000. 097 097 093 093 095 090 25 800. 098 098 094 094 097 092 24 630. 100 100 096 096 098 094 23 500.0 100 100 097 098 099 095 22 400.0 103 103 099 100 102 097 21 315.0 104 104 096 100 104 098 20 250.0 104 103 101 100 103 098 19 200.0 101 101 097 097 103 098 18 160.0 098 100 097 098 101 096 17 125.0 098 098 096 094 098 093 16 100.0 097 099 093 089 094 089 15 80.0 097 096 089 089 093 090 14 63.0 100 097 088 087 091 085 13 50.0 092 094 085 085 090 086 12 40.0 098 094 081 078 080 077 11 31.5 109 105 091 085 089 084 10 25.0 087 084 073 074 075 070 9 20.0 078 073 062 063 067 061 8 16.0 076 072 067 064 061 060 7 12.5 073 071 062 061 061 060 6 10.0 074 069 061 060 060 060 5 8.0 076 071 062 060 060 060 4 6.3 072 067 067 060 060 060 3 5.0 073 064 065 060 060 060 2 4.0 071 065 061 060 060 060 1 3.15 068 061 067 060 060 060

♦Decibel reference .0002 microbar

86

IWiV

AFAPL-TR-70-80

Blodt AngU 42c

Flop Angle 5^ RPM 700

Fllttr Number

Center Frequency

Microphone Numbers | 1 2 3 4 5 6

jb db* db db db db db

40 Overall 921 922 117 118 120 115 39 20,000. 070 068 061 063 069 060 38 16,000. 079 079 070 069 080 071 37 12,500. 089 089 084 082 091 084 36 10,000. 095 095 091 089 098 091 35 8,000. 097 097 094 092 099 094 34 6,300. 097 099 096 094 100 095 33 5,000. 099 101 097 095 101 096 32 4,000. 100 102 098 096 102 098 31 3,150. 101 103 099 098 103 099 30 2,500. 102 103 100 099 103 099 29 2,000. 103 104 101 100 104 100 28 1,600. 103 105 102 101 104 100 27 1,250. 105 106 103 103 105 101 26 1,000. 106 108 104 104 106 102 25 800. 106 109 106 106 107 102 24 630. 108 111 107 108 108 104 23 500.0 107 111 109 110 109 105 22 400.0 109 113 110 110 111 107 21 315.0 110 113 108 110 111 107 20 250.0 110 112 109 109 112 107 19 200.0 107 109 105 105 111 107 18 160.0 104 110 106 106 107 104 17 125.0 107 109 109 105 105 100 16 100.0 107 107 100 099 103 098 15 80.0 106 105 098 101 105 102 14 63.0 098 098 089 090 097 093 13 50.0 118 115 099 092 101 094 12 40.0 109 106 092 089 096 091 11 31.5 092 088 084 081 085 076 10 25.0 091 085 078 075 084 072 9 20.0 089 082 069 068 081 065 8 16.0 089 081 069 069 080 062 7 12.5 086 080 069 067 084 060 6 10.0 084 079 067 068 079 060 5 8.0 080 074 063 064 077 060 4 6.3 079 074 064 066 076 060 3 5.0 074 073 060 067 078 060 2 4.0 071 068 063 069 074 060 1 3.15 067 071 063 063 073 060

♦Decibel reference . 0002 microbar

87

,

WIII»l>w"'I^W"P«IW»W»B»»^»»il|i i|» »I

AFAPL-TR-70-80

Blodt Anglt 42°

Flop Anglt jr RPM 957

FIKtr Number

Center Frequency

Microphone Numbers I

1 2 3 4 5 6 Jk

db* db db db db db

40 Overall 127 127 123 124 127 124 39 20,000. 080 080 080 080 080 080 38 16,000. 084 084 082 082 087 082 37 12,500. 095 095 093 093 098 094 36 10,000. 101 101 100 100 105 101 35 8.000. 102 103 101 102 106 103 34 6,300. 103 104 103 103 107 105 33 5,000. 105 105 104 104 !08 106 32 4,000. 105 106 104 105 109 107 31 3,150. 107 107 105 106 111 108 30 2,500. 108 108 106 107 111 108 29 2,000. 108 109 107 108 111 109 28 1,600. 109 109 108 109 112 109 27 1,250. no 111 109 111 113 110 26 1,000. 111 112 110 112 114 111 25 800. 111 112 111 112 114 112 24 630. 113 113 112 114 116 113 23 500.0 113 113 113 115 116 114 22 400.0 114 114 113 115 118 114 21 315.0 114 114 110 114 118 114 20 250.0 112 114 111 112 117 114

19 200.0 112 113 110 110 116 113 18 160.0 112 115 112 113 115 112 17 125.0 118 117 113 111 113 111 16 100.0 107 111 107 110 114 111 15 80.0 108 109 105 103 107 101

14 63.0 125 125 118 114 114 111

13 50.0 106 106 101 101 104 099 12 40.0 101 103 097 098 104 089 11 31.5 099 097 093 095 102 085 10 25.0 094 095 091 095 100 083

9 20.0 091 095 090 092 099 082 8 16.0 087 091 087 089 099 081 7 12.5 085 088 085 086 097 081 6 10.0 083 086 083 083 096 080

5 8.0 080 080 080 080 095 080 4 6.3 080 080 080 080 094 080 3 5.0 080 080 080 080 092 080

2 4.0 080 080 080 080 091 080

1 3.15 080 080 080 080 090 080

♦Decibel reference , 0002 microbar

88

-"' ^—7~.

AFAPL-TR-70-80

AMBIENT

Filter Number

Center Frequency

Microphone Numbers

1 2 3 4 5 6

db* db db db db db

40 Overall 072 073 073 073 073 072 39 20,000. 060 060 060 060 060 060 38 16,000. 060 060 060 060 060 060 37 12.500. 060 060 060 060 060 060 36 10,000. 064 062 964 062 063 062 35 8,000. 060 060 061 060 060 060 34 6,300. 060 060 060 060 060 060 33 5,000. 060 060 060 060 060 060 32 4,000. 060 060 060 060 060 060 31 3,150. 060 060 060 060 060 060 30 2,500. 060 060 060 060 060 060 29 2,000. 060 060 060 060 060 060 28 1,600. 060 060 060 060 060 060 27 1,250. 060 060 060 060 060 060 26 1,000. 060 060 060 060 060 060 25 800. 060 060 060 060 060 060 24 630. 060 060 060 060 060 060 23 500.0 060 060 060 060 060 060 22 400.0 060 062 060 063 060 063 21 315.0 060 060 060 062 061 061 20 250.0 060 060 060 061 060 060 19 200.0 060 060 060 060 060 060 18 160.0 060 060 060 060 060 060 17 125.0 060 060 060 060 060 060 16 100.0 060 060 060 060 060 060 15 80.0 060 060 060 060 060 060 14 63.0 069 069 070 070 070 070 13 50.0 060 060 060 060 060 060 12 40.0 060 060 060 060 060 060 11 31.5 060 060 060 060 060 060 10 25.0 OSO 060 060 060 060 060 9 20.0 060 060 060 060 060 060 8 16.0 061 060 061 060 062 060 7 12.5 062 061 062 061 062 061 6 10.0 060 060 060 060 060 060 5 8.0 060 060 060 060 060 060 4 6.3 060 060 060 060 060 060 3 5.0 060 060 060 060 060 060 2 4.0 060 060 060 060 060 060 1 3.15 060 060 060 060 060 060

♦Decibel reference .0002 microbar

89

AFAPL-TR-70-80

REFERENCES

1. Gerald T. Cafarelli and Matthew H. Chopin, Computer Program for Reducing Static Propeller Test Data. ASD Technical Report 68-19, Aeronautical Systems Division, Wright-Patterson Air Force Base, Ohio, June 1968.

2. Matthew H. Chopin, Propeller Static Performance Tests for V/STOL Aircraft. Part 1 - Summary Report, ASD Technical Report 69-15, Aeronautical Systems Division, Wright-Patter son Air Force Base, Ohio, January 1970.

3. Peter A. Franken and Edward M. Kerwin, Methods of Flight Vehicle Noise Prediction. WADC Technical Report 58-343, Wright Air Develop- ment Center, Wright-Patterson Air Force Base, Ohio, November 1958.

90