oo MEASUREMENT AND ANALYSIS ^ OF NOISE FROM … · ^ AIRCRAFT IN LEVEL FLIGHT - ... level flybys at altitudes of 6000, 1000, and 200 feet. Measurement sites on the ground were at

FAA-RD71-98

oo MEASUREMENT AND ANALYSIS ^ OF NOISE FROM SEVENTEEN ^ AIRCRAFT IN LEVEL FLIGHT -■ (MILITARY. BUSINESS JET, AND ^ GENERAL AVIATION)

:.:^ Carole S. Tanner

HYDROSPACE RESEARCH CORPORATION 1360 Rosecrans Street

San Diego, California 92106

transpolJJJ^ U.S. International Transportation Expositior

Duties International Airport Washington, D.C.

May 27-June 4, 1972

D D C Reproducvd by NATIONAL TECHNICAL INFORMATION SERVICE

Springfield, Ve. 33191

NOVEMBER 1971

FINAL REPORT c

Availahilily is unlimited. Document may be released to the National Teelmical Information Service, Springfield, Virginia 22151. for sale to the puhlic.

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION

Systems Research and Development Service Washington, D.C. 20591

^i

The contents of this report reflect the views of the Hydrospace Research Corporation, which is responsible for the facts and the accuracy of the data presented herein. The contents do not necessarily reflect the official views or policy of the Department of Transportation. This report does not constitute a standard, specification, or regulation.

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TECHNICAL REPORT STANDARD TITLE PAGE

T. Report Ne.

FAA-RD-71-98

?. Govtrnmant Acc»tsion No. 3. R«cipi*nt'i Catalog No.

TR-S-212 4. T„i,.n<i sub.i.i. MEASUREMENT AND ANALYSIS OF

NOISE FROM SEVENTEEN AIRCRAFT IN LEVEL FLIGHT (MILITARY, BUSINESS JET, AND GENERAL AVIATION)

5. R*por) Dot*

NOVEMBER 1971 6. Psrforming Organization Cods

7. Author'i)

CAROLE S. TANNER

6. Performing Organization Report No.

9. Porforming Organization Norn« and Addroti

HYDROSPACE RESEARCH CORPORATION 1360 Rosecrans Street San Diego, California 92106

10. Wnrli Unit No.

550-002-07H 11. Contract or Grant No.

DOT FA70WA-2374

12. Sponsoring Agency Nome and Addret«

FEDERAL AVIATION ADMINISTRATION Systems Research and Development Service 800 Independence Avenue, S.W. Washington. D.C. 20591

IS. Typo o( Roport and Poriod Covorod

FINAL REPORT June 1970-November 1971

14. Sponsoring Agoncy Codo

15. Supplomontary Notos

16 Abtlroct

Measurements of noise from aircraft level flyovers are presented in the form of effective perceived noise level (EPNL) as a function of slant range at the closest point of approach. Seventeen aircraft were investigated (various military, business jets, and general aviation types) and the effort involved acquisition of acoustical, meteorological, aircraft tracking, and aircraft operational data. Microphones were locited near the ground in an array nor- mal to the flight track. All tests were conducted at the Pendleton Municipal Airport, Pendleton, Oregon, during two separate time periods in July and October 1970.

17. Koy m»,4* ACOUStiCS Aircraft Noise Effective Perceived Noise Level Noise Noise Transmission Path Sideline Noise Propagation

I' So.ur.l, C lotll ot *•« ro»orll

UNCLASSIFIED

V. iocur.l. Clot»! lot !•<■•

UNCLASSIFIED

II. DnHikulion Stoio~Of.r

Availability it unlimited. Document may be released to the National Technical Information Service, Springfield, Virginia 22151, for sale to the public.

II. No ol Potoi

61

». P..

Vmlm* Form DOT F 1700.7 {■•••i

TABLE OF CONTENTS

Page

INTRODUCTION

APPARATUS AND METHODS

Aircraft Description

Flight Profile Description

Acquisition of Operational Data

Test Area

Noise Measurements

Data Reduction and Analysis

Atmospheric Observations

DISCUSSION OF RESULTS

Aircraft Performance

Atmospheric Observations

Noise Measurements

SUMMARY

REFERENCES

PricHiil Mil Mill Hi

LIST OF ILLUSTRATIONS

Figure Page

1 Radar Tracking Unit 5

2 Test Site 7

3 Phototheodolite Unit 8

4 Location of Microphones for July Tests 9

5 Location of Microphones for October Tests 10

6 Noise Acquisition System 11

7 Slant Distance as a Function of Base, Height, and Elevation Angle 11

8 HRC In-House Facilities, Model 1360 12

9 System Frequency Response 12

10 Weather Aircraft 14

11 Sounding Profile 14

12 Aircraft Sounding (5 October 1970) 15

IS Aircraft Sounding (6 October 1970) 16

14 Aircraft funding (7 October 1970) 17

15 Aircraft Sounding (8 October 1970) 18

16 Noise Level of Cherokee 6, 100-Prrcent Power 25

17 Noise Level of Cessna 337, 100-Percent Power 26



20 Noise Level of DC-9, 75-Perrent Power 29

21 Noise Level of DC-9. lOO-Prrrenl Power 30

22 Noise Level of Sabreliner, 70-Percent Pnwer 31

23 Noise Level of Sabreliner. 75-Pi'rc<>nl l^mer 32

24 Noise Level of Sabreliner. 80-lo 82-Perrent Pwwcr 33

25 Noise Level of Sabreliner, 90-Perrenl Power 34

IV

LIST OF ILLUSTRATIONS, Contd

Figure Page

26 Noise Level of Jet Commander, 87.5- to 88.5- Percent Power 35

27 Noise Level of Jet Commander, 92-Percent Power 36

28 Noise Level of Jet Commander, 94- to 96-Percent Power 37

29 Noise Level of Learjet, 78-Percent Power 38

30 Noise Level of Learjet, 84- to 85-Percent Power 39

31 Noise Level of Learjet, 100-Percent Power 40

32 Noise Level of T-33, 100-Percent Power 41 33 Noise Level of C-141A, 75-Percent (Inboard)/88-

Percent (Outboard) Power 42

34 Noise Level of C-141A, 82- to 83-Percent (Inboard) 90- to 91-Percent (Outboard) Power 42

35 Noise Level of A-7B, 85- to 86-Percent Power 43

36 Noise Level of A-7B, 88-Percent Power 44

37 Noise Level of A-7B, 100-Percent Power 45 38 Noise Level of F-4, 85-Percent Power 46

39 Noise Level of F-4, 100-Percent Power 47

40 Noise Level of F-101, 86- to 87-Percent Power 48 41 Noise Level of F-101, 100-Percent Power 49 42 Noise Level of F-102, 55-Percent Power 50

43 Noise Level of F-102, 100-Percent Power 51

44 Noise Level of F-102, Afterburner Power 52

45 Noise Level of F-8K, 93-Percent Power 52

46 Noise Level of F-8K, 96- to 97-Percent Power 53

47 Noise Level of t -8K, Afterburner Power 54

48 Noise Level of A-6A, 75-Percent Power 55

Figure

49

50

51

LIST OF ILLUSTRATIONS, Contd

Noise Level of A-6A, 87- to 89-Percent Power

Noise Level of A-6A, 98- to 100-Percent Power

Noise Level of A-4C, 75-Percent Power

Page

56

57

58

LIST OF TABLES

Table

I Aircraft Description

II October Test Flights

in July Test Flights

IV Meteorological Parameters - October Tests

V Aircraft Flight Performance, Military Aircraft

VI Aircraft Flight Performance, Business Jet Aircraft

VII July Meteorological Conditions, General Aviation Aircraft Tests

Page

4

6

6

13

21

23

24

vl

I

LIST OF SYMBOLS

Symbol Definition Unit

X Horizontal distance perpendicular to runway centerline feet

Y Distance from reference point along runway centerline feet

Z Height above reference point feet

Distance from aircraft to microphone at closest point of approach feet

Angle between ground plane and slant range to aircraft degree

vtl

INTRODUCTION

In an effort to obtain information to serve as a data base for the effective perceived noise levels of noncommercial jet and turboprop aircraft, a series of tests were conducted at Pendleton, Oregon, in July and October 1970.

The July tests recorded the noise levels of the Cessna 182, 337, 210, and Piper Cherokee propeller-driven aircraft and T-33 military aircraft. The noise from two level flybys, at altitudes of 100, 700, and 1500 feel for each aircraft except the T-33, were recorded on the ground at distances of 500, 1000, 5000, and 2000 feet perpendicular to the line of flight. The T-33 flew at altitudes of 100, 700, 1500, and 2000 feet above the ground. The October tests recorded the noise levels of military and business jets from level flybys at altitudes of 6000, 1000, and 200 feet. Measurement sites on the ground were at distances of 110, 500, 1000, 1500, 2000, 2500, 3000, and 3500 feet perpendicular to the flight path. The aircraft were tracked using an MPS-19 radar operated by a crew from Edwards Air Force Base, Califor- nia, and by a portable theodolite system operated by a crew from the National Aviation Facilities Experimental Center, Atlantic City, New Jersey. Mete- orological data was acquired by a crew from EG&G Environmental Division.

The test conditions and details of measurement instrumentation used in obtaining the acoustic, meteorological, tracking, and aircraft performance data are discussed in the following sections.

APPARATUS AND METHODS

AIRCRAFT DESCRIPTION

The general description of each aircraft tested is given in Table I. The test gross weights of the military aircraft were all somewhere below maximum takeoff gross weight since these aircraft were deployed from their home base. The nonmilitary aircraft flybys were started at or near the maximum takeoff gross weight.

FLIGHT PROFILE DESCRIPTION

Flight procedures utilized straight and level flybys down the centerline of the runway. Each flyby was started upon reaching a VOR marker approximately 3. 6 n. mi. from the beginning of the runway and terminated over the outer marker 4 .1 n. mi. from the end of the runway. A racetrack pattern was used. OctDber flyby altitudes were 6000, 1000, ancl 200 feet above the nominal field altitude of 1500 feet mean sea level (MSL). The October tests were performed in the sequence outlined in Table n. The July tests were performed in the sequence outlined in Table ITI.

ACQUISI'I'ION OF OPERATIONAL DATA

The operational data acquired consists of aircraft performance parameters and tracking information. During the course of each flyby, the pilot noted such parameters as aircraft weight, outside air temperature, percent power, and indicated airspeed.

The aircraft spat:e positioning performance was obtained by tracking the aircraft with a radar and a phototheodolite system.

The radar, a modified MPS-19, is shown in Figure 1. Rada:::- tracking outputs consisted of digital tapes and analog plots of the X, Y, and Z coordinates of the aircraft. Since the aircraft was not instrumented with a beacon, the aided t r a c k i n g mode was utilized . This mode of operation was visual tracking of the aircraft with the aid of a long-range television camera. Aircraft range was obtained from skin reflection. The selected visual point of reference was the aircraft wing root.

Preceding page blank

3

Table I. Aircraft Description

i Aircraft Engine

Total Maximum Power

at Sea Level (lb thrust)

Nominal | Gross Weight

(lb) !

A-4C PtW J52-P-8A 9,300 24 500

{ A-6A PltW J52-P-8 9,300 80.600

F-8K PfcW J57-P-20 18.000 29.500

F-102 P4W J57-P-23 18,000 27,000

F-101 PftW J57-P-55 16,900 51.000

F-4 GE J79^JE-8 17,000 56,000 !

A-7B P4W TF30-P-6 11,350 42,000

C-H1A PliW TF33.P-7 21.000 318.000

T-33 J33-A-35 S,200 12.000

I.urj.t GE CJ610-6 2.950 13.500

.In Commander GE CJ610-I 2.850 20.000

Suhrrlinrr PtW .IT12A-8 3.300 20.300

DC-9 PAW ,IT8D-9 14.500 77.700

C.SMU 182 Con 0-470-R 230 hp 2.950

CCKSIU 210 Con I0-52OA 285 hp 3.800

CrsHna 337 Con 10-360-C 210 hp 4.630

Chrrukt-v 8 Iv. 0-540 K4B5 280 hp 3.400

The phototheodolite units were comprised of two Ackley cameras located as shown in Figure 2. The instrument, shown in Figure 3, is an optical tracker having a movie camera triggered electronically at the rate of two frames per second. The film field of view includes the target and azimuth and elevation dials. The location of the theodolites perpendicular to the runway requires the assumption that the aircraft is flying down the centerline.

Both the radar and phototheodolite data were reduced to yield the appro- priate coordinate values. In this report, X coordinate is crossrange, Y coordinate is downrange, and Z coordinate is height above the reference point. The reference point was chosen as the intersection of the runway centerline and a line passing through the microphone positions.

Tracking data output consisted of both hard copy and digital tapes.

TEST AREA

Tests were conducted in the vicinity of the Pendleton Municipal Airport, Pendleton, Oregon, during the months of July and October 1970. Acoustic data was acquired during the July tests at the four sites shown in Figure 4. Two microphones are located at each site, one at ground level and the other at a height of 26 feet directly above the ground microphone. The odd-numbered microphone is at ground level and the even-numbered microphone is 26 feet

Figure 1. Radar Tracking Unit

in the air. The eight sites used during the October 1970 tests are shown in Figure 5. These microphones were located at a height of four feet above the ground. During both tests, the ground surface was fallow except site 1 in Figure 4 and sites 1 and 2 in Figure 5. The ground surface here consisted of a thin layer of soil over rock.

NOISE MEASUREMENTS

The noise measuring instrumentation used in these tests is illustrated in the block diagram in Figure 6. The condenser microphones were fitted with windscreens and positioned with the diaphragm parallel to the ground. There- fore, the angle of incidence varied according to the test altitude and microphone position, as shown in Figure 7. The microphone output was recorded on a 14- channel FM tape recorder. Time correlation between all operational units was achieved through the use of an IRIG B time code, synchronized to WWV. The field calibrations included recording anelectrical tone at each of the one- third octave band center frequencies and the periodic recording of a 94-dB acoustic signal at 1000 cps. During these tests, preemphasis of the high frequencies was used.

Table II. October Test FliKhts

Aircraft With Afterburner Aircraft Without Afterburner

Run No.

AIIMud* Abuvr MSI •

(Ml Tkrual

7M0 100

2500 Alli-rtwrnrr

2M0 loo 2500 7»

1700 100

ITOO 7»

1100 M

RIM AliMwt»

Al- .. MM • (ill

Ii . .. ( 1

TV» 1 100

7V10 n 2M0 IU0

2M0 n 1100 100

1700 n

' i 1701 1 M

•Hun»4y Rk/alkM IMW II MM •Hun«4> I I. wli.... ISM 11 UNI

DATA REDUCTION AND ANALYSIS

Data reduction consisted of on-line processing of a selected microphone during the test and off-line processing at San Diego. The on-line processing was performed by the system described in Reference 1. The San Diego in- house system is shown in Figure 8. The total system response wasdetermined by processing the calibration tapes. A typlcil system response is shown in Figure 9. An angle of incidence correction was applied to each site.

The system hardware and software conform to the requirements of FAR Part 36, Reference 2. The reduction of acoustic data conformed to the requirements of Reference 2, with one exception. This exception relates to the correction of acoustic data to a standard day temperature of 77 F and 70- percent relative humidity.

Table III. July Test nights

Run 1 No.

Alllludi- Abovr MSI •

(«)

1 1 ThruM

3500*• .00

JS00" 100

3000 100

3000 100

2200 100

2200 100

1100 100

two too

* Kiiim.iv Flrvallon ••T-33 Only

I MM II MSI

During Initial processing of data, it was noticed that some test day EPNL values, when corrected to standard day, were yielding unrealistic answers. Further investigation Indicated that these problems of over correction oc- curred when the measured aircraft noise level spectrum was being limited by the background and/or system noise level. This background noise can be defined as one or a combination of: 1) environmental ambient noise, 2) data acquisition system noise, and 3) data processing system noise.

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Since a large portion of the data was acquired at slant range distances in excess of those en- countered in a noise certification test for which Part 36 is designed, an alternate method of applying the atmospheric absorption corrections was necessary in order that the results would be meaning- ful. The method chosen consists of comparing the spectrum at the time of maximum tone-corrected perceived noise level (PNLTM) withthe last spectrum acquired in the processing routine. The last spectrum was selected because of its availability at the end of the sound pressure level acquisition routine, and except for low frequencies, is a good measure of the background noise. When the difference between the spectrum at PNLTM and the background, at frequencies greater than 400 cps, is equal to or less than 3 decibels, the atmospheric absorption correction consists of the alpha value used for the last band having a

signal-to-noise ratio greater than 3 decibels. The comparison of the first ten bands is ignored because the last spectrum may consist of low frequencies attributable to the aircraft.

Figure 3. Phototheodolite Unit

It is recognized that this is a conservative method in that atmospheric absorption corrections are being made to spectrum levels not associated with the aircraft.

Other methods of solution to this particular problem are discussed in de- tail in Reference 3.

ATMOSPHERIC OBSERVATIONS

The meteorological parameters acquired during the October tests are summarized in Table IV. Three types of weather observations were made: 1) surface, 2) radiosonde, and 3) aircraft soundings.

8

MICROPHONE 7 & 8

500FT

r-- MICROPHONE 5 & 6 ~--H·l-

500FT

MICROPHONE 3 & 4

NOTE: ODD NUMBERED MICROPHONES LOCATED NEAR GROUND LEVEl .

EVEN NUMBERED MICROPHONES LOCATED 26 FEET ABOVE THE GROUND.

Figure 4. Location of Microphones for July Tests

The surface observations consisted of data acquired at three towers located as shown in Figure 2. In addition, wind velocity and direction were acquired at ea~h microphone location.

Data was continuously recorded on strip charts at the towers during the entire test period. Data was extracted from these charts at the time of day associated with the closest point of approach of the aircraft to the line of microphones. The data was averaged over 2 minutes.

Radiosonde balloons were launched periodically during the test day . In general, these soundings provided data representative of each particular test

9

rt MICROPHONE 8

5B-OI MICROPHONE 7

50 FT I L_}- MICROPHONE 6

JFTi -1----¥-- MICROPHONE 5

5BOJFT I 1 ~MICROPHONE 4

500FT

~MICROPHONE 3

soL~ ,-- MICROPHONE 2

I~

NOTE: ALL MICROPHONES LOCATED FOUR FEET ABOVE THE GROUND .

MICROPHONE 1

------· -~ DIRECTION OF FLIGHT

Figure 5. Location of Microphones for October Tests

10

6 tN e ... z 0 i= < > lol ..I lol loo 0 t.l ..I 0 z <

TYPICAL STATION ,------~------------ - -. I TWISTED SHIELD PAIR

I v~--~

I B&.K 4134 B&.K 2619 B&K 141 JUNCTION MAIN I MICRO- PRE- FIELD UNIT ROX J UNCTION

PHONE AMPUnER I sox I I I ~~--~ L ___________________ __ ~

Figure 6. Noise Acquisition System

100

0 JULY TESTS 90 !:::. OCTOBER TESTS

80

70

60

50

40

30

20

10

0 100 200 500 1000 2000

SLANT RANGE AT CPA (FT)

Figure 7. Slant Distance as a Function of Base, Height, and Elevation Angle

11

AMPEX 1300 TAT-£ RECORDER

5000 10000

Figure 8. HRC In-House Facilitie s , Model 1360

35

~ <( t:O 30 ::l.

C\1 0 25 0 0

6 4l 20 ~

t:O ~ 15 ;.~ en z 0 10 p.. U}

4l 5 0:::

::E 4l E-< 0 U} ,_..... f;; ....

/

- 5 50 100 200 400 1000 2000 4000 10000

FREQUENCY (HZ)

Figure 9. System Frequency Response

12

'Iable IV . Meteorological Parameters - October Tests

,...--

I Temperature I ! Type Relative Wind Wind Elevation Freque ncy of Humidity Velocity Direction (ft} Measureme nt

r----I

I X ! X 50 - 2500 Befor e every run Aircraft

Radiosonde I X X X X 0 - 3000 Bi -t.u Jrly

Surface I

! X X X X 6 Continuously

Surface X X X 50 Conti nuously

Surface X X X 50 Continuous ly

Surface X X X 50 Cont inuously

Surface X X X X 100 Continuously

Surface X X 26 Every run

Surface X X X X 10 Houri.'

' I j ______ - l

period. The balloon was launched to the south of the test site at the location shown in Figure 2. The balloon transponder was tracked via a radar. The radiosonde yielded temperature and dew point, averaged over 6-second inter vals. Winds aloft were calculated fr om changes in balloon position, from one tracking point to the next.

Upper air soundings were also made using the aircraft shown in Figure 10 . This aircraft flew a sounding profile shown in Figure 11. Meteorological instrumentation included a Cambridge Systems Model 137-C /137-83 P hygrometer .

The results of the aircraft soundings are shown in a series of graphs in Figures 12 through 15. The atmospheric absorption corrections for October data were calculated from ARP 866, Reference 4, using the temperature and relative humidity data from the central tower at the 50-foot elevation.

13

j

_J

llt'\f\1\1'"

--Figure 10. Weather Aircraft

6000~------------------------------------------------~r--,

/

REFERENCE POINT

OL_--~~--~~~~====~~--~----~----~ -12000 -8000 -4000 0 4000 8000 12000 16000

DISTANCE ALONG GROUND (FT)

Figure 11. Sounding Profile

14

;:::: ... . ,. < ~ ::::> a:: t.: ;-.. 0 Q

< £-:: Q :.: ::

E :;: ~ 4000 ::::> a: :.J > g < 2000 £-::

6000

4000

2000

50

A~1BIENT TE MPERATURE (° Fl ri E l AT!V F llD1!1)1TY 1 l

a. A-6A Tests

\-1

60 iO 1!0 90 100

AMBIENT TEMPERATl:RE (0F) REI ATIV E Hl'Mli)ITY ('-l

b . F-8K Tests

Figure 12. Aircraft Sounding (5 October 1970)

15

~ ;>o < ~ z ::::> a: "' > 0 Ill < !-

~ "' =

4000

2000

60 70 80

AMBIENT T EMPERATURE (°F) RELATIV E H UMIDITY ("; )

E ;>o <

a. F-4 Tests

6000 r-----.---.--.--..,.---...----,

~ 400&

c:: :.J > g '( 2000 !-

o~~-~-~-~--~~ 20 30 40 50 70

AI\IOIE!\T TE~IPERATl:RE ("n HE LATIVF IIU\ImiTY I )

b. F -102 Tests

60001r-~---,.---,--..,.---..---,

80 90

AMil!ENT TEMPERATl"nE tn H ELAT!VE Hl":\IIOITY 1'. )

c . C-141A Tests


16

100

90

:><: ~ 4000 ::::> a: t.l g ..; lOOO 1-:c 0 i;i :c

i=" "" > <: 3: z ::::> a: t.l :> g <: 1-:z: 12 :.J =

> <

0 20

6000

4000

2000

0 20

6000

~ 4000 ::::> a: t.l :> g < 2000 1-= 12 t.l :c

30 40 50 20 40 60 80 100

AMBIENT TEMPERATURE (°F) RELATIVE HUMIDITY (i-l

a. DC-9 Tests

30 40 50 20 40 60 80 100

AMBIENT T EM PERATURE (°F) RELATIVE HUMIDITY ("0)

b. F-101 and A-7B Tests

20 40 60 80 100

AMBIENT T EMPERATURE (°F) RELATIVE HUMIDITY ('(. )

c. A-4C Tests

Figure 14. Aircraft: Sounding (7 October 1970)

17

<

i

M 40 M>

AUBirNT TFMPERATl RE ÜF

iO «0 TO HO

RELATIXE HtMIDITY i I

a. Learjet-23 Tests

30 40 SO

AMBIINT TEMPERATl RE "F

^0 80 TO HO

RELATIVE HI MIDITY

b. Jet Commander Tests

•vVW

AMBIENT TEMPERATUR^ i"ri

60 TO «0

RELATIVE HIMiniTV I

■in ion

c. Sabreliner Tests


18

DISCUSSION OF RESULTS

AIRCRAFT PERFORMANCE

The performance of the aircraft during the flyby operations is indicated by the tabulated results in Tables V and VI for the October tests. These values were obtained from the pilot test cards. No data was available from the July test of general aviation aircraft.

The altitude profile and lateral deviation track of the test aircraft over the runway was an average of 200 feet, based on an examination of the radar analog plots.

ATMOSPHERIC OBSERVATIONS

Summaries of the October prevailing meteorological conditions are given in Figures 12 to 15 for the aircraft tested. This data indicates an erratic and large variation in relative humidity as a function of altitude. This is due to the unstable air mass moving through the area during the test period. Precipitation was present during this time period.

The July prevailing meteorological conditions for the general aviation aircraft are shown in Table VII. Aircraft soundings and radiosonde data were not available for this date. Atmospheric absorption corrections were based on the surface measurements provided by the airport weather bureau.

NOISE MEASUREMENTS

The results of the flyby noise measurements obtained during the July tests for the general aviation aircraft are presented in Figures 16 to 19. Figure 16 shows a comparison of the noise levels as measured by the microphone at 26 feet above the ground and by the ground microphone. Due to the large variation between these data, only those data measured by the microphone located 26 feet above the ground are presented in Figures 17, 18, and 19.

Data for the business jet aircraft is presented in Figures 20 to 23. The results for the military aircraft are given in Figures 24 to 51.

19

The data is presented in subsets for /} > 15 degrees and £ < 15 degrees, where possible, for each range of power settings. Each subset is composed of data at specific flyby altitudes and microphone locations. The flyby altitudes given on the figures are the heights above the reference point. In addition, the surface weather conditions are given on each figure. Note that the wind speeds were in excess of 10 knots for a large portion of the data.

20

Table V. Aircraft Flight Performance, Military Aircraft

Aircraft

MSL*** Altitude

(ft)

Aircraft Weight

(lb) OAT* ( C)

Power (%)

IAS** (kt) Date of Test

A-6A

F-8K

F.4

F-102

C-141A

7500 7300 2500 2500 2S0C 1700 1700 1700 1700

7500 2500 2500 2500 1700

7500 7500 2500 2500 2500 1700 1700

6500 2500 2500 2500 1700 170u

7500 7500 2500

42,000 41.500 40.700 40.100 38.600 37.600 37.200 36.700 35.600

25.000 24.500 24.000 23.500 23.000

44.000 43,000 42.000 41.000 40.000 39.000 38,000

29.500 28,000 27.000 26,400 25,300 24.600

168,000 163.000 161.000

♦ OAT ■ Outside Air Temperature ** IAS = Indicated Airspeed ♦♦*MSL = Mean Sea Level

• 10 5

• 25 • 15

15 »37 • 20 • 15 • 15

4 •4 • 4 .4 • 4 4

• 4

-1 • 3 3

.3 4

.4

0 '0 .9

100 75

100 75 80

100 75 89 98

97 A/B

97 93 96

100 85

A/B 100 85

100 85

100 100 100

55 100 55

82/90 75/88 83/91

440 190 475 230 135 510 240 130 220

170 170 170 140 150

480 180 560 540 180 550 180

280 240 210 170 210 170

170 180 180

5 October 1970

5 October 1970

6 October 1970

6 October 1970

6 October 1970

21

Table V. Aircraft Flight Performance, Military Aircraft, Contd

MSL*** Aircraft Altitude Weight OAT Power IAS

Aircraft (ft) (lb) CO (%) (kt) { Date of Test

F-101 7500 46,000 -1 100 420 7 October 1970 2500 48,000 • 4 100 420 2500 44,000 •-4 87 220 1700 43,000 )8 100 430 1700 42,000 • 8 86 210

A-7B 7500 24.500 • 7 100 220 7 October 1970 7500 24,250 »7 88 165 2500 23,900 t7 100 220 2500 23,550 • 7 88 165 2500 23.200 7 85 135 1700 22,850 7 100 200 1700 22.500 7 86 160 1700 22,150 I 84 128

A-4C 7500 16.000 7 100 450 7500 15,800 7 75 330 2500 15,000 7 100 480 2500 14.800 7 75 320 2500 14.400 7 75 120 1700 14.200 7 100 380 1700 14.000 7 75 450 1700 13.800 7 75 140 2500 13.600 7 75 500

T-33 3500 14,000 No 1C 0 155 14 July 1970 3500 13,500 Data 153 3000 13,000 160 3000 12.500 159 2200 12.000 163 2200 11.500 181 1600 11,000 168 1600 10,500 |

1

169

J

Table VI. Aircraft Flight Performance. Business Jet Aircraft

MSL Altitude

Aircraft 1 Weight OAT Power IAS

Aircraft (ft) (lb) ( C) ro) (kn Date of Test

DC-9 7500 77.250 100 200- 350

7 October 1970

7500 76.350 - 75 220- 350

2500 i

75.340 - 100 240- 350

2500 74.250 - 75 160- 330

2500 73.200 - 75 127- 130

1700 72.100 - 100 170- 350

1700 71.350 - 75 172- 320

1700 70.350 - 75 138- 128

Lear)et-2^ 7500 12.300 100 250 8 October 1970 7500 11.900 88 118 2500 11.500 19 too 260 2500 10.900 14 85 140 2500 10.500 14 78 105 1700 10.100 17 100 230 1700 9.700 15 84 100

Jet Commander- 8800 15.800 . 1 96.5 180 8 Orl«*er 1970 1121A 6900 15.400 9X5 140

2500 14.900 95.0 180 2500 14.600 915 154 2500 14.100 87.5 115 1700 13.600 94.0 180 1700 13.000 915 166 1700 15.000 11 88.5 120

Sabrelmer - 60 6000 17.000 . 7 90 180 8 October 1970 8000 16.600 82 174 2500 16.100 90 180 2500 15.900 82 174 2500 15.500 70 128 1700 15.100 90 180 1700 14.900 80 155 1700 14.500 75 120

23

Table VII. July Meteorological Conditions, General Aviation Aircraft Test«

Ambient Temoerature

rr) Relative Humidity

Aircraft Run Number ft)

Chrrokee 6 60.0 45 60.5 42 61.0 43 60.0 44 60.5 43 60.5 43 61.0 44

CeMM 210 60.5 45 62.0 42

10 60.5 45 11 61.0 43 12 62.5 43 13 63.5 40 M 63.5 40 15 64.0 40

Cewiu 182 16 72.0 29 11 72.5 31 11 72.5 30 It 73.0 29 20 . 21 73.5 28 22 72.5 28

C«MM 231 22 75.5 28 24 76.5 27 H 78.5 27 26 . 27 77.0 27 28 78.0 28

24

I >

f. i

■

Ü 1 «1

no

KM)

•

{ i

1 1 ' 1 1 1 M II ' WEATHER AT 10 FEET

TEMPERATl'RE 60-il F RELATIVE HLUIMTY. 42-4S'.

HI)

T n

WIND SPEED.. . ..«-t KT

itil

■

i 1 0| 8 \

70 MIC HUPHONts

60

0 AT 26 FT ABOVE GKOl'ND r O ON THE GROUND

IM mil 200 MM 1000 2000 &U00

SLANT RANGE AT CPA FT

IUO00 20000

K

a. >

z >

> U

no

100

90

HO

M

a. /? > 15 ; Z = 700 Feet

r 6 a

^1—' I I I Ml WEATHER AT 10 FEET

TEMPERATURE .60-61 F RELATIVE HUMIDITY. 42-45 WIND SPEED 4-9 KT

MICROPHONE»

1 AT 16 FT ABOVE GROUND ^ ON THE GROUND

J-J. ILLii MM» 10000 20000

SLANT HAM.» AT CPA (FTi

b. <? < 15 ; Z = 100 Feet

Figure 16. Noise Level of Cherokee 6. 100-Percent Power

110

a I x u 100 J Id > i 3 " 90

a u > üi

u a. u >

u Ul u. hi Ul

80

70 —

*%

ALTITUDE

O 1500 FT D 700 FT

00

'b

' I ' I I I 11II—^" WEATHER AT 10 FEET

TEMPERATURE 75.5-78 F RELATIVE HUMIDITY.. .27-2«fl> WIND SPEED 9 KT

500 1000 2000 5000

SLANT RANGE AT CPA(FTI

10000 20000

a. /J > 15°; Z = 1500 and 700 Feet

110

E u 100 J u > u 9

c Ul > u C ce u a u > P u Ul u. u. Ul

90

80

70

60 200

c ) >

' I ' ! II II II ' 1 WEATHER AT 10 FEET

TEMPERATURE 75.5-78F RELATIVE HUMIDITY . . . 27-28,"c J

I T T

1 **.

WINI )SPI :ED 9KT j

[ o c >

> J

[ j

_i 1 500 1000 2000 5000


10000 20000

h. ß < 15 •, Z = 100 Feet

Figure 17. Noise Level of Cessna 337, 100-Percent Power

26

110

I & ■ 100 J u > 9

o c > 3 y K U a. M > P U w u, u

90

80

70

60

1- ■ i ■ i i i 11 ii ' i

WEATHER AT 10 FEET 1

TEMPERATURE 60.5-64 F RELATIVE HUMIDITY. . .40.45'n J

[ WIND SPEED 11-14 KT 1

V f 1 Ql

J

1 AL TITl DE r J

1 o r D

1500 700

FT FT

J _- 200 500 1000 2000 5000

SLANT RANGE AT CPA (FTI

10000 20000

a. /? > 15 ; Z = 1500 and 700 Feet

no

so

E g 100

u > u

5 I q > w y cc ill a. u > P y u u. u. u

90

80

70

60 200

' I ' I I l IIII ' WEATHER AT 10 FEET 1

TEMPERATURE 60.5-64 F RFI.ATIVF. HIIMiniTY. ..40-45% J

[ WIND SPE ED 11-14 KT |

i < >

J

[

< >

0 < ) ■1

J

500 1000 2000 5000


10000 20000

b. /3<15 ; Z = 100 Feet


27

•4

no

I 100 ■I > B ■3 u '■Ü 90

Q u > ü DC W a.

> P U g u.

80

70 —

60

• i ■ i i 11111 i WEATHER AT 10 FEET j

TEMPERATURE 72-73.5 F RELATIVE HUMIDITY... 28-31% J

[ WIND SPEED 9KT j

[ T

0 fl^

AL Tin DE

B #0 \

Q r ° 1500 700

FT FT

- _ 200 500 1000 2000 5000


10000 20000

a. /? > 15°; Z = 1500 and 700 Feet

110

s E S 100 •A u > u 3 H 75

a u > Q Q K U a. u > P u

90

80

70

60 200

' I ' 1 1 1 1 1 M WEATHER AT 10 FEET j

TEMPERATURE 72-73.5 F RELATIVE HUMIDITY... 28-3l'ro J

I WINI )SPI ED 9KT |

\ \ \

J

1 ' \ J

\

L_ _ 500 1000 2000 5000


10000 20000

b. /? <150; Z = 100 Feet


28

X z. u

120

110

7 100 3 z

u ü

ü a E

90

HO

70

' I ' ! I I M M WEATHER AT 50 FEET

TEMPERATURE 37-42 F RELATIVE HUMIDITY. ..B^gffo .

< i

4 | c

WIND SPEED.. .2-7 KT

■

1] a oo

a a •

AL T1TI DE

°0nS, a •

O 6000 FT □ 1000 FT ^ 200 FT

.1.1 _

!

k -

200 500 1000 20(0 5000

SLANT RANGE AT CPA (FT'

10000 20000

a. /3 > 15°; Z = 6000, 1000, and 200 Feet

120

z M Uli

y. urn 5 s

'Ml

U MU

70 200

WEATHER AT 50 FKET

TEMPERATURE 37-42 F RELATIVE HUMIDITY. .8.1-99. WIND SPEED 2-7 KT

-o—^

o '•

tOO 10U0 2000 5000

SLANT RANGE AT CPA I FT^

_L ludOu 20000

b. /? < 15 ; Z = 200 Feet

Figure 20. Noise Level of DC-9, 75-Percent Power

29

120 I I I I I I I I

c:: WEA THE!\ AT 50 FEET ., z. c. !!! 110 ..l Cal >

TEMPERATURE . .•.•• •• 37-42 F RELATIVE HUMIDITY .•• 84-99"0 WIND SPEED .•• . •.... . . 2-7 KT

~ Cal ..l

~ tOO

~ ~ Cbc

[

c Q :.; > :;:

90 ~

cc u

~ Cal > != 80 u Cal

'"' '"' Cal

ALTITUDE

~~ r-- - ---

0 11000 FT 0 1000 FT 6 200FT

I I 1 7~oo ;,oo lC!OO 20ll0 ;,000 h.lf)<ll) l OOM

SLANT flA NGE AT CPA (FTl

a. ~ > 15 o; Z = 6000 .. 1000, and 200 Feet

120

Ci ;z a. ~

w ::. :.:l ..J

:.: "' 6 :.: Q .... > :..1 u c:: w c. J t.l > 1= 80 u Cal

"" '"' I. ,.

70 I , 00 5011

SLANT HAI\'GE AT Cr ,\ CFT)

b. n < 15 " : Z = 200 Feet

Fig·ure 21. Noise L"vel of DC-9 100-Perc-ct t P o 'Jf':O

30

120

M a. u. 110 ■1 u >

s. 5 I 2

a:

100

90

HO

1 TEN REL

n i iMM • 1 WEATHER AT 50 FEET

PERATURE ATIVE HUMIDITY

. 51-53 F

. 47.SR'T J

V WINDSP EEC ■ 2-5 KT

[ t r o

[ 1 0

0 o

i J

j

[ 0

_- tm

200 500 1000 2000 S000

SLANT RANCK AT TPA (ITl

10000 2000(1

/3>15t; Z = 1000 Feet

Figure 22. Noise Level of Sabreliner, 70-Percent Power

31

120

I K H no

s

u -I X

100

M

r so

— 1 '1 1 1 1 III ' WEATHER AT 50 FEET !

TEMPERATURE 51 -53 K RELATIVE HUMIDITY.. .47-55', J

p WIND SPEED 2-5 KT \

[ Q \

[ \

_ J _ 200 500 1000 2000 5000 10000 20000

SLANT RANGE AT CPA FT)

a. ß >15\ Z = 200 Feet

120

■ 110 —

100 3 y.

-tu

MO

\

; i i t i i i i )


TEMPFRATI'RF 51-IS F RE1.ATIVF HIIMIDITS' . At.lfP, 1

\ I WIN D Si» EED ..

1

|

2-S KT !!

\ I

J

i j i

1 i 5

> 1 1 i

M i

I ; i 1

<

| 1

KKHI 21111(1 -IOOO

SLANT HANGE AT CPA FT

lillKI'l

b. /? < 15 , Z - 200 Feet

Figure 23. Noise Level of Sabreliner, 75-Pprcent Power

32

a 1 a, B J

> u -1

O I Q

> Ü U cc u a. u > P U u u. u. U

.120

110

100

90

80 —

70 200

L -n ' 1 ' 1 M 1 III ' 1


TEMPERATURE 51-53 F RF.I.ATI VR HIIMiniTV . . . il.^^i

k WIND SPEED .. . 2-5KT 1

[ a fa a «

J

AI TITl JDE

a a

3a 0

9 ■1

o S

1 i I

4500 FT 1000 FT 200 FT

. 1 1 1

500 1000 2000 5000

SLANT RANUK AT CPA (FT)

1U00Ü 2000(1

a. /? > 15 ; Z = -iSOO, 1000, and 20«» Feet

120

a. ¥ 110 J > u

» 100 5 x.

B 90 i u K H > G 80 B •J.

k u

70 200

■^ " ^

' 1 ' i 1 1 M i 1 1 WEATHER AT 50 FEET 1

TEMPERATURE 51-53? _ RELATIVE HUMIDITY... 47-55' J

[ WIN D SP EEt ■ 2-5KT |

[ c )

-1

[ o

c ,0< i

J

h

» _ J 500 1000 2000 5000

SLANT RANGE AT CPA (PT1

10000 20000

b. /3< 15 ; Z = 200 Feet

Figure 24. Noise Level of Sabreliner, 80- to 82-Percent Power

33

120

W 110

U

100

80 -

70 200

r

' I ' 1 I I 1 Ml " 1 WEATHER AT 50 FEET |

TEMPERATURE 51-53 f RP.I.AT1VR HIIMiniTV . . . il-V-T. A

\

b. -a

WIND SPEEC . 2-5KT

\ a i

a n 0

j

AL TITL DE

a b J

-

OD

O

4500 1000 200

FT FT FT

.

4

500 1000 2000 iOOO

SLANT RANGE AT CPA 'FT:

100UU 20000

a. i3 > 15 ; Z = 4500, 1000, and 200 Feet

120

110

>

^3 100 3

u u fi 3 E u > P u u a. u.

90

HO

200

[ i

' i ■ i : i i M ; • | WEATHER AT 50 FFET j

TEMPERATURE 51-53 1 | RELATIVE HUMIDITY . . . 47-r.r.' 1

[ WIN D SP EED . 2-;-iKT !

\

i 1

0 >

i

1 i

i l i

J

\ o< >0 j

|

L- - _ ,

1 1 ,! i _J . _«-i

I ■ 1

lu0<i 2000 nu

SLANT RANGE AT CPA IT

20 )' I

b. ^ < 15 ; Z = 200 Foot

Figure 25. Noise Level of Sabrelirer. 90-PercPnl P'^'cr

34

1. a u

_] U

Id

s s

> U u £ Ed a.

P u u C u. U

120

110

100

90

80 -

' I ■ 1 I I I III ■ WEATHER AT 50 FEET J

TEMPERATURE 47-51 F HKI.AT1VE HIIMiniTY. .. .1!)-Sfi'; J

r i 1 c s>

WIND SPEED ,. 0-6 KT

\

u O o

o J

AL TITD DE

Ö 30 J

0 1000 L D 200

FT FT

- 200 500 1000 2000 5000


10000 2000(1

a. /3 > 15 ; Z = 1000 and 200 Feet

120

-a Z a. w 110 -1 w > M -J

* 100 5 z

U > u u OB u; a.

(- U u u. u. Ed

'(0

80

70 200

' 1 ' 1 I 1 ! 1 11 " I WEATHER AT 50 FEET

TEMPERATURE 47-51 F RELATIVE HUM1D1TV... JO.IK J

l WIN nm m ).. • 0-«KT ;

[ 3 0

( > 0

j

[ < >o

_ ■ L 500 1000 2001) 5000

SLANT HANCE AT CPA (FT

I illKII i 20001)

b. 0 < 15 ; Z = 200 Feet

Figure 26. Noise Level of Jet Commander, 87.5- to 88.5-Pcrcent Power

35

Q

"' z c. ~ ..:I :...: > :... ..I

toJ Ill

5 z Q :..l > ~ u c: Col c. to: > t:: u toJ :... :... to:

120

l 110

100

90

80 ~ AL'!'ITYtn:

70 200

0 540'l FT 0 !000 FT

I I I -~oo

I I I I I I I I I

WEAntER AT 50 FEET

TEMPERATURE .•...... 47-51" F RELATI VE HUMIDITY .• . 49- 56r;, WIND SPEED • . • . • • . •. • . 0 - 6 KT

r:P 0 _r

0

0 0

I 0 le ~ I

;

I I' 11 I I

1000 2fl00 500(1 100110 <'0001!

SLANT llA."r.E AT CPA 1FT )

fJ > 15 o ; Z = 5400 and 1000 Feet

Figure 27. Noise Level of Jet Commander , 92-Per cent Power

36

~ ~ ..1 :.; > :.; ..1 :.;

"' c z :;: > :;; g :.. c. :.. > i= w :.; ... :.. :.;

Ci ~ Clo ~ ..1 ... > ... ..1 ... rn 0 z

s > 1:3 (J

= ... Clo ... > I= (J ... "' "' ...

120

110

100

90

80 ~

70 200

6

It~

ALTITUDE

0 5300 FT 0 1000 FT 6 200FT

I I I 500

I I I I I I I I WE~THER~AT 50 FEET

TEMPERATURE • • . .•. .. 47- 51" F RELA1'1VE HUMIDITY o •• 49-56% WIND SPEED •• • ••..• . • . 0-6 KT

a:IC

I c .n

c PC 0

IGc

1000 2000 5000 10000 20000

SLANT RANGE AT CPA CFT)

a. 13 > 15 o; Z = 5300, 1000, and 200 Feet

120

110

100

90

80

70 200

I I I I I I I I I

WEATHER AT 50 FEET

TEMPERATURE • . .. o o. o 47-51° F RELATIVE HUMiDITY . .. 49-56% WIND SPEED ... ........ 0-6 KT

0 0

p 0

0

500 1000 2000 5000 10000 20000


b. 13 < 15°; Z = 200 Feet

Figure 28. Noise Level of Jet Commander, 94- to 96-Percent Power

37

120 I I I I I I I I

a .W...fu\THE~~T.!!O FEET

2 =-~ 110 .J

TEMPERATURE . . . .• .• . 44-47• F RELATIVE HUMIDITY . • • ~ 1 -58'-. WIND sPEED . . . . .. . .. . · 10-15 KT

til > til .J til 100 'A

0 z Q tw > ~ 90 u

II ~(

0 I 0 a:: til 0 =-til :: t; 80

0 p til

'"' '"' :.l

0 I i 1 I

7~0 500 1000 2000 5000 IOOfJu 20fJ00


fJ > 15 °; Z = 1000 Feet

Figure 29. Noise Level of Learjet, 78-Percent Power

38

120 I I I I I I I I

iii WEATHER AT 50 FEET

~ Cl. ~ 110 ..J

TEMPERATURE . .. . .••. 44-47" F RELATIVE HUMIDITY .. • 51-58% WINO SPEED . . ... .. . . • · 10-15 KT

t&l > Lil ..J 0 ~ 100 s ;z; Q Lil > w 90 u

0 ~~ 0

n II: Lil 0 Cl. Lil > j:

80 u t&l

"" "" t&l

- ALTITUDE 0 p

0 0 1000 FT 0 200FT

I I I 7~oo 500 1000 2000 5000 10000 20000

SLANT RANGE AT CPA !FTl

a. f3 >15 °; Z = 1000 and 200 Feet

120 I I I I II II I

iii ~EA THER AT 50 FEET

~ Cl. ~ 110 ..J

TEMPERATURE ..•..... 44-47' F RELATIVE HUMIDITY .. . 51-58% WINO SPEED ..... .. ... . t0-15 KT

t&l > t&l ..J

~ tOO

i Q I t&l > w 90 u

p II: t&l Cl.

0 )

t&l > j:

80 u 0

t&l

"" c~ o "' t&l

500 1000 2000 5000 10000 20000


b. f3 < 15 o ; Z = 200 Feet

Figure 30. Noise LE'vel of Learjet, 84- to 85- Percent Power

39

0

110

no

mo

S «o as u a.

HO —

70 200

1 A n

tL

' I ' 1 I 1 M 1 1 WKATIIKR AT 50 FEET 1

TEMPERATimE 44-47 F . RELATIVE HUMIDITY... 51-r)H; J

A 0D

0 WIND SPEED

1 1

1 1

. 10-15 KT

I I

o id

r

1 i

]

Al .TIT! roi

T

1

J

o GOOO 1000 200

FT FT FT

1 u- u 1000 2000 1000

SLANT RANOE AT CPA (ITl

IOOO0 20000

a. 3 > 15°; Z = 6000. 1000, and 200 Feet

i ' i Ml WEATHER AT 5t

1 1 !

FEET a - i — 2.

TSMPERATURE . .44- 17 110 . . RELATIVE MIMIDin .. 51- r)ti J

WIM) SPEED ...10- 15 KT rf] ! 1 1 1 1 l I -* - 1 J iai 11 j ! J 1 1 1 M 100 r» _ _ IM i t 4 i ■ 1 -' 0 1 i 1 1

, i l | 1 J u , i > -^ o i 1 •A* J i i i 1 N =: 1

J* . 1 O 1 | | 1

U ! 1 1 1 -^ 1 - HI,

1 1 1 I i - 1 1

a. 1 4. ' 1 I

1 II

1 III i j

70 : . I . i Ml 7i HI rniM |M 20 10 .)OlM) ■■ 2(HI

N 1 wr vwi;}- ATC >A IFT

b. Ö < 15 ; Z = 200 Foot

Figure 31. Noise Level of Learjet. 100-Perrr?Tt Power

40

120

es

a w no j u > u

2 U > Üü ü X u

H > P o M E u, U

100

90

80 —

70 200

L r ^-

V

TEMI HE LA

11 Mim iTEATHER AT 10 FEET

'ERATURE 59-63 F TIVE HUMIDITY...50-52,. J

h \ i

WIND SPEED . .3-5 KT j

\ r°D •1

Al .TITl JOE J

1 0 D

o

2000 1500 700 100

IT FT FT FT

_l

J

500 1000 2000 5000


10000 2Ü00U

a. 3 > 15 ; Z = 2000, 1500, 700, and 100 Feet

120

•o z

SS no -i u >

u Ü B U a.

i- o u E u. u

100

BO

80

200

i '— ' 1 ' 1 III WEATHER AT 10

TEMPERATURE RF.I.ATIVF HUMiniTV

II "I FEET J

...59-63°F i

...50-52', J

L WINE SPE ED 3-5 KT

\

( >

0 c »

J

[

^_ _. _ 500 1000 2000 5000

SLANT RANGE AT CPA I FT)

10000 20000

b. /?< 15 ; Z = 100 Feet

Figure 32. Noise Level of T-33, 100-Percent Power

41

120

i no

u 3 " 10G 3 I

u u B g > P u

E

90

HO

70 200

'I'll I 1 IM ' WEATHER AT 50 FEKT

TEMPERATURE 42-43 F RELATIVE HUMIDITY...76-78% _

■

WIND SPEED 8 KT

• •

■

o ■

_J

■

500 1000 2000 5000


100ÜÜ 20000

/3 > 15°; Z = 6000 Feet

Figure 33. Noise Level of C-141A, 75-Percent (Inboard)/ 88-Percent (Outboard) Power

120

3. u J 111 >

O

3 U > u u a a.

> p U u E u. u

110

100

90

80

70

nn

' 1 ' 1 1 II 1 WEATHER AT 50

TEMPERATURE RELATIVE HUMIDITY

11 FEET

..42-43 F

■

a CD

a

WIN) 3SP) •JED .6 KT

■

□ a

t

■

AI „TITl JDt

5 i •

o . D

fiOOO 1000

FT FT

10000 20000 200 500 1000 2000 5000


/3 > 15 ; Z = 6000 and 1000 Feet

Figure 34. Noise Level of C-141A, 82- to 83-Percent (Inboard) 90- to 91-Percent (Outboard) Power

42

a. u J u 5 u ■3

X a u > u o ce u E u > P Ü u E E u

no

100

a

' I ' 1 ! I 1 I I I

WEATHER AT 50 FEET

TEMPERATURE iS-ii'F RELATIVE HUMIDITY. . .67-80^

• a 0 o

WIND SPEEE .3-6 KT

M

80

70

•

0

0

0

•

AL T1TI IDE

0 0 0

■

0 1000 FT . D 200 FT

— 200 500 1000 2000 5000


10000 20000

a. /? > 15 ; Z = 1000 and 200 Feet

120

z 0. U UO

u > u J

B loo 5 a u > u o X u E H > P O u E E u

90

HO

70 200

■

' I ' 1 Mil WEATHER AT 50


1 FEET

.43-45 F

. 67-80'o

•

\

WINI a spi JED 3-6 KT

• o c »

0 <; »O

■

■

_ u- 500 1000 2000 5000


10000 20000

h. ß< 15 ; Z =200 Feet

Figure 35. Noise Level of A-7B, 85- to 86-Percent Power

43

1201—r-

Ä

a H

> w 3

no

^ 100

2 u > v u * E > b ü E E

90

80 ALTITUDE

O 6000 FT D 1000 FT

701 i L-L. 200

WEATIIEH AT 50 FEET

TEMPERATURE 43-45 F RELATIVE HUMIDITY . .67-80 WIND SPEED 3-6 KT

tr

4J 500 1000 2U00 5000


10000 20000

ß > 15°; Z = 6000 and 1000 Feet

Figure 36. Noise Level of A-7B, 88-Percent Power

44

120

z E w 110 J td > U -J Id 2 100

s > u u K a.

> h U

ki U

90

HO

70

r t

TEV HEL

■ I M I I 11 ' | WEATHER AT 50 FEET

PERATURE AT1VE HUMIDITY. .

.43-45 F

.67-80» 1

\ £

a a

WIND SPEEE .3-6 KT j

•1

\

a a

a a J

\ Al TITl IDE

3

<r \

j

c>ao

6000 1000 200

FT FT FT

1 ~- _

r _J

J

200 500 1000 2000 5000


10000 20000

a. /?> 15 ; Z = 6000, 1000, and 200 Feet

120

a i s y no -i H > U J u 22 100

Q u > 1 U R U -

Ü E u. u

110

HO

70 200

- ■II 1 1 1 1 WEATHER AT 50


I ' 1 FEET 1

..43-45 F

..67-80'r J

[ 0

WIN DSP EEC .3-6 KT i

\ < ) o

f )

j

\ 0

J

— ■ . J 500 1000 2000 5000


loooo 20000

b. /3< 15 ; Z = 200 Feet

Figure 37. Noise Level of A-7B, 100-Percent Power

45

uo

U 120

Q a

S

Ü u E Hi u

no

100

90 -

200

■ i ■ i i i i i i i i

WEATHER AT 50 FEE 1 j

TEMPERATURE 40-41 F RELATIVE HUMIDITY. . .70-71n J

r — n

WIND SPEED 10-13 KT 1

\

& a a

a a i K

j

AL T1TI Di:

A ID 0 I

|o j

A

i .

6000 1000 200

FT FT FT

_J .. _ _ L

]

SOO 1000 2000 :'i0(H)

SLANT RANGE AT (PA IFT)

IniiDi, 20(100

a. /3 > 15 ; Z = 6000, 1000, and 200 Feet

5 s

U

(-

130

120

110

100

0(1

[ r r 1 1 ' 1 MM

WEATHER AT 50

TEMPERATURE. ... REIJVTIVE HUMIIJITY

1 l FEET 1

..40-41 F

..70-71'ö J

[ WIN DSP BED..

1 j 1

10-13 KT I

i 1 i

[ < >

o

J

S >

0 < »0

J

L. - _i ^ ̂ H

200 500 1000 20(10 5000 10000 20000

SLANT RANfJF AT (PA H Tl

b. /? < 15 ; Z - 200 Feet

Figure 38. Noise Level of F-4. 85-Percent Power

46

E u j u > u 3

o R u > g K U E

u

1JU r- ■ i ■ i i i i i ■ i i

WEATHER AT 50 FEET |

TEMPERATURE 40-41 F i

20 . RELATIVE HUMIDITY.. .70-71 n J WIND SPEED 10-13 KT ]

110

100

■ o

i -1

■ i j

0

4 j AL1ITUDE

0 6000 FT D 200 FT J

•0 1 | 1.1 —J _LJ

200 S00 1000 .000 5000

SLANT RANGE AT (PA IKTI

1Ü00U 2()()()(i

a. ^ > 15 : Z = 6000 and 200 Feet

v.

Ü w

ISO

120

110

mo

90

HO 200

[ ' I ' I MM

WEATHER AT 50

TEMPERATURE . RELATIVE HUMIDITY

I FEET j

..40-41 F

..7o-7i; J

[ 3

WIN1 ISP EtO 10-13 KT 1

1 ! I

0 c >

J

[ 0

< i

0

j

■i L . - _ — - u 500 1000 2000 5000

SLANT RANDE AT CPA (FTi

IOOOO

b. /? <15 ; Z = 200 Feet

Figure 39. Noise Level of F-4, 100-Percent Power

47

i W

u 3 U

MU

vi 100 3

u

u e u.

00

HO —

70

p

■ 1 ' 1 1 1 1 1 M |

WEATHEH AT SO FKK I J

TKMPEHATinu: 43-45 F . RELATIVE HUMIDITY...G7-80V J

I a c »

D

O

WIND SPEED

1

3-fi KT ;

i 0 0

o L J

\ AI -T1T1 JDK

O J

r D 1000 200

FT FT

1

200 500 1000 2000 5000


10000 20000

a. /? > 15 ; Z = 1000 and 200 Feet

to

-1 u > U J

120

no

* 100

i £

u x a U > P u

90

HO

70 200

• i ■ i ii i11: i WEATHER AT 50 FEET

TEMPERATURE 43-45 F ' RELATIVE HUMIDITY . . P7-H0 '. J

0

WIN DSP '.EV ., .3-fi KT j

k o D J

[ o , >0 J

I _J _ _

J

50U 1000 2J0U f)U00


lOOilu 2cnK)n

b. ß<15 ; Z = 200 Feet

Fipure 40. Noise Level of F-101, 86- to 87-Percent Power

48

130

I E 9 120 >J M > 3

I u > u ■ u E

F u e u. u

110

100

90 —

80 200

-~ ■ 1 ' 1 1 M III ' 1 WEATHER AT 50 FEET J

TEMPERATURE 43-45 F . RELATIVE HUMIDITY... 67-80 r J

0

c c 9 1 0

WIND SPEEC .3-6 KT |

[ o

o \

AI .T1TI JDK

0 1000 FT L D 200 FT

_ _

\

500 1000 2000 5000

SLANT RANGE AT CPA (FTl

10000 20000

a. /?> 15 ; Z = 1000 and 200 Feet

130

EB ■a Z. E a 120 j u > u 9 I 110 5 I Q u > B u K u a H > Ü B E E M

100

90

80 200

TEV . REL

r ' 1 I TTT11 ^-1 WEATHER A F 50 FEET j

PERATURE 43-45 F ATIVE HUMIDITY... 67-80 i 1

3

WIN DSP EEC .3-6 KT j

V 0 1

o

J

[ 1

o J

J

500 1000 2000 5000

SLANT RANGE AT CPA (FTl

10000 20000

b. /?< 15 ; Z ■ 200 Feet

Figure 41. Noise Level of F-101, 100-Percent Power

49

= i Cl. ~ .J Ill > Ill .J Ill VI

a z Q Ill :: Ill c.> a: Ill Cl. Ill > i= c.> Ill

"" "" Ill

iQ ., z Cl. ~ .J Ill > Ill .J til VI a z Q Ill > l;j c.> a: til Cl. til > i= c.> til

"" "" til

120 T 1 1 1 1 1 1 1

,WEATHER AT 50 FI::E l

TEMPERATURE ... .. . .. 40-41 F

110 RELATIVE HUMIDITY . .. 72-78"0

0 WIND SPEED . •.... . . .• . 6-10 KT

100

'"' 00

0 90 0

0 00 0

80 ~ ALTITUDE

7'bo

120

110

100

90

80

70 200

0 1000 FT 0 200FT

I I I 500 1000 2000 sooo 10000


a. (3 > 15 o; Z = 1000 and 200 Feet

1 I I I I I I I YfEA '!"t'~R AT 50 FEE~

TEMPERATURE ........ 40-41 F RELATIVE HUMIDITY ... 72-78"0 WIND SP EED .. . ..... ... 6-10 KT

c

...,

p 0

p

500 1000 ~000 5000 10000


b. f3 < 15° ; Z = 200 Feet

20000

20000

Figure 42. Noise Level of F -102 , 55-Percent Power

50

= "C z c. ~ ...1 ::.l > Eo: ...1 ::.l <I)

0 z Q ::.l > i;i u a: ::.l c. ::.l > i= u ::.l

"" "" ::.l

= "C z c. ~ ..J WJ > WJ ..J

WJ <I)

~ Q ::.l > i;i u a: ::.l c. ::.l > != u ::.l

"" "" WJ

130

120 ~

110

100

ALTITUDE 90 ~ ---

80 200

0 5000 FT 0 1000 FT c. 200FT

I I I 500

~

I I I I I I I I

'J!EA THER AT 50 FEET

TEMPERATURE .... . . . . 40-41 F RELATIVE HUMIDITY . .. 72-78% WIND SPEED ..... . .... . 6-10 KT

IC 0 []

Cl oo 0

_...., .... gf ~ c)

1000 2000 5000 10000 20000

SLANT RANCE AT CPA (FT)

a. f3 > 15 o; Z = 5000 , 1000 , and 200 Feet

130

120

110

100

90

80 200

I I I I I I I I WE.\THER AT 50 FEET

TEMPO: ltl\ TURE .. . . . ... 40-41 F RELATIVE HUMIDITI • . . 72-78"0 Wll'l> SPF.iW . . .... . . .• . 6-10 KT

I I I I

0

0

p

0

)O

500 1000 2000 5000 10000 20000

SLANT RAI\GE AT C PA (FTl

b . {3 < 15 n; Z = 200 Feet

Figure 43. Noise Level of F-102 , 100-Percent Power

51

c ~

f ~ ....) Ill > Ill ....)

"' "' a z Q

"' > i:i u a:: ~

"' c: ... u "' II. II.

"'

130

120

110

100

90

80 200

I

I I I I I I I I WE~'nfER AT 50 FEET

TEMPERATURE . •• • •. • • 40-41 F RELATIVE HUMJOITY ... 72-78% WIND SPEED . • .• • • •. • •• 6-10 KT

lc 0 0 0

00 oo

500 1000 2000 5000 10000 20000

SLANT RANGE AT CPA (FT )

f3 > 15 o ; Z = 1000 Feet

Figure 44. Noise Level of F -102 , Afterburner Power

~ ~ z Q.

~ ....)

"' > :.J ....)

"' "' a z Q

"' ;:-. w u a::

"' Q.

"' c: ... u

"' II. II.

"'

120

110

100

90

80

70 200

I I I I II II ~EATHER AT 50 FEE_!

TEMPERATURE .••...• . 49 F RELATI VE HUMIDITY . . . 58-6o"' WIND SPEED .• . ... . . .•. 18-22 KT

p 0 0

c 00

0 c

500 1000 2000 5000 10000 20000

SLANT RANGE AT CPA ( fT)

f3 > 15 o; Z = 1000 Feet

Figure 45. Noise Level of F-8K, 93-Per cent Power

52;

Q .., z c. ~ ..J

"' > "' ..J

"' en 5 z 0 ;w

2: l&l u a: l&l c. ~

2: i-u ;w

"" "" l&l

120

I I

T T T I I I I I ~ATHER AUO FEET

TEMPERATURE .. . . ... . 49 F

110 RELA TlVE HUMIDITY ... 58-6o't> I ~' 0

0 WIND SPEED . ... . . ..... 18-22 KT

c p c 0

100

0~ 90

80 r ALTITUDE

70 200

120 .,

11 0

100

90

80

70 200

0 1000 FT

I c 200 FT

I I I 500 1000 2000 5000 10000 20000

SLANT RANCE AT CPA (F'T)

a. {3 > 15° ; Z = 1000 and 200 Feet

I I I I I I II

WEATHER AT 50 FEEI

TEMPERATURE ... . .. . . 49 F RE.LA TIVE HUMIDITY ... 58-6o"' WIND SPEED . .....•.... 18- 22 KT

p 0

) 0

0

500 1000 2000 5000 10000 20000

SLANT RANGE AT C PA ( f'T )

b. {3 < 15 o ; Z = 200 Feet

Figure 46. Noise Level of F-8K, 96- to 97-Percent P ower

53

-

I

-

:

11»

100

■

r^ — r— r- WEATHKR AT 50

TEMPERATURE , RKLAT1VE HllMlt)IT>'

FKET j

..49 r '

..58-60 j

D< > o 0

WIN

o ) bV KKU , .

1 IH-ii M 1

■

i )o J

HO

70

]

m L_

J

20Ü son 1000 200(1 5000

SLANT PANGE AT CPA iFTi

10000 20000

/? > 15 . Z = 1000 Feet

Figure 47. Noise Level of F-8K, Afterburner Power

54

110

2 a 9 loo ■i B > B 9 H « 90

u >

Ü IS u - > P u

HO

70 — ALTITUDE

O 6000 FT D 1000 FT ^ 200 FT

601—1- 200

J_L

1 I ' I I I I I I ! '— WEATHER AT 50 FEET

TEMPERATURE 50-51 F RELATIVE HUMIDITY...64-70^ WIND SPEED 15-17 KT

'%

500 1000 2000 5000

SLANT RANGE AT CPA IFTI

10000 20000

a. *? >15 ; Z = 6000, 1000, and 200 Feet

110

B 100

> u 3 ft 90

a > u X 3 c

u

HO

H E E 70 u E

60 200 500 1000 2000 5000

SLANT RANGE AT CPA (FTi

[ WEATHER AT 50 FEET 1

TEMPERATURE 50-51 F RELATIVE HUMiniTV. .fi4-7tfn J

[ WIN DSPI SED ,,

1 1

15-17 KT |

[ »

0

I C

o j

1 —i

i

_J _ 10000 20000

b. ß<l5 \Z = 200 Feet

Figure 48. Noise Level of A-6A. 75-Percent Power

55

120

8 MO u u -i

Q u E u u Ä U a. a >

u E h.

100

90

80

70

" " ' 1 ' ! M I 11! ' 1 WEATHER AT 50 FKtT 1

TEMPERATURE 50-51 F | RELATIVE HUM1D1TV. . .64-70';> J

ll

3 0 o

O 0

WIND SPEED .15-17 KT

[ 00

oo J

A LTIT UDE

J

1 O 1000 FT 1 D 200 FT

200 500 1000 2000 5000


10000 20000

a. /? > 15 ; Z = 1000 and 200 Feet

120

a i E * 110 ■J Id > u -I

I 100

a > S u x

u >

o

u. U

90

80

7U 200

' 1 ' 1 1 1 1 1 i 1 1 WEATHER AT 50 FEET

TEMPERATURE 50.51F RELATIVE HUMIDITY. . .64-70 r J

[ WIN D SP EED , ,

1 i

15-17 KT |

< > o

c 1 j

I o

c 1 0 ■1

[ ^_u

500 1000 2000 50ÜU

SLANT RANGE \T(PA iFTi

urnoo 20000

b. ^ < 15 ; Z - 200 Feet

Figure 49. Noise Level of A-6A, 87- to 89-Percent Power

56

130

B ?. E S "20 ti Id > w 9 n 110

C u > Ü CJ K u a H > P O S E b. U

100

80

D TEft REL

1 ' 1 1 I 1 111 ' 1 WEATHER AT 50 FEET

IPEKVFURE 50-'il F ATIVi' HUMIDITY.. . 64-70'r J

[ a

Qoo

WIND SPEI D . . .15-17 KT 1

I 0

o 0

<|

Al Tin JDE

o j

1 0 L a

1000 200

FT FT

— 200 500 1000 2000 5000


10000 20000

a. /J > 15 ; Z = 1000 and 200 Feet

130

Z

u 120

> B

" no

a u > 0 100 fi u E u > u

u. u

90

80 200

■ I' I I 1 11II ' WEATHER AT 50 FEET

TEMPERATURE 50-51 F RELATIVE HUMIDITY... 64-70T- J

I < >

WIN) ]SPI :ED 15-17 KT

[ Oo

o j

[ ( i

O J

[ J

500 1000 2000 5000


1000(1 20000

b. /?<150; Z = 200 Feet

Figure 50. Noise Level of A-6A, 98- to 100-Percent Power

57

i u

5 2 U > w Q x Q E

120

no

100

90

F 80 -

I 70

200

ALTITUDE

O 6000 FT □ 1000 FT A 200 FT

.1.1

ib. 0°

1 I ' I I I I 111—"" WEATHER AT 50 FEET

TEMPERATURE 46-47 F RELATIVE HUMIDITY.. .62-65^ WIND SPEED 4 KT

CO QG □ 30.

500 1000 2000 5000


10000 20000

a. /3 > 15°; Z = 6000, 1000, and 200 Feet

I a. H

J

> J

120

no

100

90

e B Ü 80 —

200

L -'■T" T rTTT

WEATHER AT 50

TEMPERATURE RELATIVE HI'MiniTV

FT ' 1 FEET |

..46-47 F j

.. 62-65 >-

[ WIN DSP KEL .. .4 KT 1

^ D

< > n

J

AI RSPE ED

1 'o.

>

J ■1

0 450 L 0 140

KT KT

_ _ 500 1000 2000 5000

SLANT RANGE AT (VA (FTi

10000 20000

b. ß <15 ; Z = 200 Feet

Figure 51. Noise Level of A-4C, 75-Percent Power

58

SUMMARY

Data is presented for a series of level flybys of military, business jet. and general aviation aircraft. Plots of eifective perceived noise level as a function of slant range at the closest point of approach are presented for elevation angles greater than 15 degrees and less than 15 degrees. This information can be used to estimate flyover noise levels for a variety of engine power settings and aircraft types.

59

REFERENCES

1. E. M. Fitzgerald, A. A. Petrini, and J. K. Zimmerman, "Real-Time Spectrum Analysis in the Field Using a General Purpose Computer, ' Hydrospace Research Corporation Technical Report, November 1969.

2. "Federal Aviation Regulations, Part 36 -Noise Standards: Aircraft Type Certification," November 1969.

3. Carole S. Tanner, "Measurement and Analysis of Noise from Four Air- craft During Approach and Departure Operations (727, KC-135, 707-320B, and DC-9),M Federal Aviation Administration Report FAA-RD-71-84, September 1971.

4. "Standard Values of Atmospheric Absorption as a Function of Tempera- ture and Humidity for Use in Evaluating Aircraft Flyover Noise/'Society of Automotive Engineers, Aerospace Recommended Practice (ARP) Re- port Number 866, 31 April 1970 (Proposed).

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Documents

oo MEASUREMENT AND ANALYSIS ^ OF NOISE FROM … · ^ AIRCRAFT IN LEVEL FLIGHT - ... level flybys at altitudes of 6000, 1000, and 200 feet. Measurement sites on the ground were at