AD ffl.PNICAL REPORT 524190 V

' LECTRIC-MOTOR WHIRL TEST OF A FLOTTORP STANDARD TVO-LAE PROPELLERAND A FLQT'TORP. STANDAIRD TWO-BLADE PROPELLER

INCORPO3RATING NEMETH AODIFNED LEADING EDGE

(Whirl Test No. 2355)

NATHAN SHOWERSfPROPELLER, LABORATORY

AUG US T 1952

Statement AApproved for Public Release

WRIGHT AIR DEVELOPMENT CENTER

ADC fNICAL REPORT 52-190

FILE copy,

~ LECTRIC-MOTOR WHIRL TEST OF A FLOTTORP STANDARD TWO-13LADE PROPELLERAND A FLOTTORP STANDARD TWO-BLADE PROPELLER

INCORPORATING NEMETH MODIFIED LEADING EDGE

(Whirl Test No. 2355)

NATHAN •'IOWERS

I PROPELLER LABORATORY

1/

AUGIUST 1952

N "---,Statement AApproved for Public Release

WRIGHT AIR DEVELOPMENT CENTER.

w -

NOTICES

*When Government drawings, specifications, or other data are usedfor any purpose other than in conne ction with a definitely related Govern-ment procurement operation, the United States Government thereby in-cursnoresponsibility nor any obligation whatsoever; and the fact thatthe Government may have formulated, furnished, or in any way suppliedthe said drawings, specifications, or other data, is not to be regardedby implication or otherwise as in any manner licensing the holder orany other person or corporationor conveying any rights or permissionto manufacture, use, or sell any patented invention that may in anywaybe related thereto.

The information furnished herewith is made available for studyupon the understanding that the Government's proprietary interests inand relating thereto shall not be impaired. It is desired that the JudgeAdvocate (WCJ), Wright Air Development Center, Wright-PattersonAir Force Base, Ohio, be promptly notified of any apparent conflict be-tween the Government's proprietary interests and those of others.

-3

pes/o~

The test propellers vmre submitted by .ereth Aeronauticallaboratory; Chicago. Illinois, for electric motor wirl testgby -Nopeiler laboratory, Aeronautics Division, AIrIght Air

LDevelo'..ment -@onter. The tbest propollers vYre the propertyof Flottorp 10-nufactur.ing Company, Grand Lapids, ,'Ichigan.The wlhirl test program vas co:nleted on 15 and 16 Mhy 1951,un.der [esearch andDevelopqent Order 5S7-4Nl, "PropellerAerodynamic Aralybis," Zhi.l lest to. 2355. M•. 1athlan bhouerswas the project en Fncecr.

:'.';AC TR 52-193ý

DISCLAIMER NOTICE

THIS DOCUMENT IS BEST QUALITY

PRACTICABLE. THE COPY FURNISHEDTO DDC CONTAINED A SIGNIFICANT

NUMBER OF PAGES WHICH DO NOTREPRODUCE LEGIBLY.

WADC TECHNICAL REPORT 52-190

ELECTRIC MOTOR WHIRL TEST OF A FLOTTORP STANDARD TWO-BLADE PROPELLERAND A FLOTTORP STANDARD TWO-BLADE PROPELLER

INCORPORATING NEMETH MODIFIED LEADING EDGE

(Whirl Test No. 2355)

Nathan ShowersPropeller Laboratory

August 1952

RDO No, 587441

Wright Air Development CenterAir ResearciJand Development Command

United States Air ForceWright-Patterson Air Force Base, Ohio

1BSTRAXCT

T e electric itotor hiltest' of a plottoro ,stanliar'" two bl.ale,si-Y ft. liarrntcr, wvood, fie-pthpro-eller rwas on 3lActol. `m-electric rmotor whirl test -was thofl condu-,ctked on a similar "St Arardilottcr2 propeoller "jab had been no]ified alon.- th oadin- ed-c by

thle Nolbnoth 2inron-aitical Labora`to7ry, Clhicag,-o, Illinois. The rnoiifica-tion consistod of a series of' smoothl inler-tations, in wave, forn., fronabout the 0.5 radius out to t~he tin, oP thle. bladle. It was claimed by

Thmoh Aeronautical Laboratory that s)eh .odali ficoat ions would increasehruist produc-(ed at any c.iven horse-po-.ror -and rpm condition.

Test data are uresented coverin,-. static calibration of the twopropellers for nompDarati-ve inurposes. Calibration consisted of themeasuremrent of the values of the thrust t-roduced and horsepoworabsorbed at various rpmn. Results of the bests wore inconclusive.

PJMLIC.,T IONj PST2T2AV

This renort has been reviewed and is approved.

Chief, Propeller LaboratoryDirectorate of Laboratories

'ADC TR 52-190ii

Pa ge

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

Purpo3e of Test . . .. . . . . . . . . . . . . . . . . 1

Procedure of Test. ... . . . . . .. . .. 1

Test Results . . . . . .. . ................. 2

Conclusions. . . . . . . . . ............................... 2

Appendix I - Cnlibration Data ............. ................. 3

Table 1 - Sound Level at Various rpm . ..... ...... ........ 5

Illustrations. .. . . . . . .. .... .................... 6

Distribution List, . ........... .. .. .. .. . . ..................... 17

YIADC TR 52-190 iv

ILLUSTI{ATIONS

Figure Page

1 Front View! ottor• Standard ro ..poller . 6

2 Front View Elottorp Standard Propeller 1 •corporatingNemwteh todil ied Leading Edge . . . .................. 7

3 Front View Close-Up of Blade- Flottorn StanO;rd Proiellr . 8

Front View Glose-Up of bladle - i ro•ttnr. Atn'ndard Prope)lDrIncorpora.ting r Ilemeth MiodifiecO Leaednth Ed _e ......... 9

5 &Ege View of Blade - Flottorp Standar:l Propeller . . . .. 10

6 Edge View of Blade - Flottorp Standa-rd PropellerIncorporating Nemeth Modified Leading FAge . . . . . . . 11

7 Horsenower Curves for Flottorp Propell .rsWhrl Test No. 2355 (First Run) . . . . .. 12

Horsepower Curves for Flottorp Propellers•hirl Test No. 2355 (Second Run) . . . .. .. . .. . . ... 13

9 Static Thnrust Curves for FlottornrrooliersW;hirl Test N1o. 2355 (First Run, . ...........

10 Static Thrust Curves for Flottorp Propcllers"Whirl Tý!st No. 2355ScndRn .... . . . . . . .1

11 Sound Level Curves for Flottorp Pro- 1]. ýrs'hirl Test No. 2355 . . . . . . 16

"'ADC TR 52-190 v

Thle 1-impeth Aceronau tical Latoratory, in a yeriJod of ti:n_ c foro the uiitOf this P recno't had boon e ietn thvarious designms of prov)-cLerbdsIn an at~t~emnit. to ipi'Yjoove porformtmco olf pr~opel-, ci's Theaix on:m tion

conisedofsytetcay reduc~ing t-hc leu,4;h of. the chor)_.d of the bladsava.-.Ious statiOrns along: the radius of the !L1adc]. 11'his -ave a -wvrlcadinŽ, edg~eplanform to t'Lhe blade.

NeehAeronau,)tica. zl Thheatory, in conference ni Niropollor Tborat-oryrpS o' no10, did net giv any, smind thoeoret:Lcal rC:ýasonl,, Lo or the i.JmprovedpefrIsc c c7a i -te e fo r this mod.Jfica~ion, but prcserted' data on iilal

mcrodtficd Model -)rpcvJclcrs. %o-,- thn'1.r or :Adhnoes h cnth Aera-4ica oator-n cocluded that such, modiLfical, ions v7ld :Lnecasc, the thrustproduced at any; !iJel 1-orsewowor ond rrm- co-ndit-ion. Thle :2icfcit:eof l4;emth Aeronau,,tical ]-kitoratoi'y -mehibitod th1em fvon aigfuill scalejinrest-I. atLion, into the problem mnd thaey appealoed to Propeller Laboratory toC..Ccnuct tht3 -test aof this report for them. 6~ufficient authoritative dat-a nvore

oroe~icd r Nmeh Arorntial 'Porator- to ini.cZ't(- thaLt conlducrt Of thetest nro,-rrnm unu be of advrnnta,-,e to th1e Air Force.

P'URPOSE~ OF Tf&ST

.IeUl ofJPt)h's test as to olhbain the static calibratio-n charact-Lstics of the 1. ubJe ct Pr1-ope C'er C, thus dete 0ýinincr the rclstivo value of the

* dex-th i-.odifications .

The "standlard" Plottorp propeller was of Design ile. '72A-L)fi1, Serial No.&~d.The propclk~r vas vrood., six ft. diasmter, fixed pitch, with a tapered

square tip planfor-im. The 'tip and outer six in. of the leading ed,,e of the* blade ;wereo protected by a metal shat *Ths propeller is illustrated W~

Figures 1, 3, and 5.

T'he second test prooelleor -was a simnilar Flottorp propeJ.llor that had booenaodif ted. along, the lead~ingi ed-e by Nemeth Aeronautical l-aboratory. Thlemodifications consisted of a series of smooth indentations, in wave form.,fri'om appro.;ximatolly the 0.3 radius out to the tip of each blade. This propel-ler had a tapered1 round tip planform instead of the tapered square tip2§anIfOr" of the "stal-dard" Flottorp propeller. The tip. and outer six in.of the leadiLn-g; edge of the blade wvere protected by a motal sh,-eatbh Thish*`Opc: 11cr and the iw~dified leading edge are illus~trated by Figýures 2, Land 6.A 110. 37)45., "Oil taper hub was us6d with Ixoth propellers.

WZOCjZDIRE OF TIM]

The subject propellers wvere inspected and assembled in preparation forvthirl testing,. Thle Whirl test program. consisted of thrust, horsepow~er and sound,calibrations at selected rpm. Calibration limitus-vere 2810O rpum or the start cf[ýblade fClutter, whnichever wvao reached first.

14VADC TH? 52-1901

TwoDC f. ;io'm~a inns i2 mh ' on am rC o. .5 ci to 2I)Curc thot thy no2tnoan M AW 'cv bc'Ozi cuatloJd Miwlo ea..1,'L±;ts~ on~ the Uttc

jXOPO own nm %a at u.; in App'dixz~ 1. a'v-s (U- corr-c~ CCCC :r:'opo..c' vwrnsu

73 t1,l j i ON ' It2C.ŽCI< U~ VCZZV1 ima ;aorlo maC rjt.oonth kC z in TO 1 I -td1vi -, .u K" bin asIt~ f v :V'ci -;nai P C1'2o? sta- ad V''< C ~ vt p 'X C 'r re

t.aI m'tt t>(C ."S,. ilusrae i,- 1CM " '', ole I or:1 Mt il'Jr:Z' 40. V I&I* m,'yoa '0 CrCCC Anca~m W ~ n W 71Y of

.''.'r'ONV 2;Io V, TO Su vl -e Vin1

i-*,oCv Itný m n O ~u1O,1.5t:TC: ~~~ ~ ~ ::- i.. 0v a~ 1 ±uane to ~ t~ uC P AILXC , X(

)-'itaQr:1 nz 'Al ( Iq ( ~ jj: f Ur '<9Ajr'C 'C to xt. o !.

1?O 52-1' ' x -90Zil~

Ti a o onzy eun on~ Pi, ýrnyllcv to insu.rc tha ithyin

1WPY o nOýWltY. in1 AppenIdix .X L *CA-vC-20 covi-cotod hico::owor ve's.zu

73Y 03.~ Y(, and 1T-' Soun 1wa rcova apa "m:,a inT'P ndj dI

i~~v.- b' . fI~ttov.lab en~co .tcr-adc 01~'~- Wth' pro! C30a * rptiorn

U11'Y~j2 I? ~ u .. >i; *... 23 VA "3ra '.2s in th*; M s: oftho tim 1=10.7s 2illustrated 1 r:'r c ii>ac ri L' ýV.y IrIE'V ac.'Ovunte for

OlMI U. :'Ji swar- .)Iarmed~e to

ýPv; 4 2-190O 2-

AAFMC- 147.WF-6.10o43-500

"WHIRL TEST No...?.35 ...............

i-DEFLETION"Tim R.P.M. H-eThut• REMARKS*

T R.P.M. Actual Correct Corrected L.E. T E. A.'l°

Calibration Data (ZiŽ's.r. itio':or'p "Sltan'3ad" d"_ rci..l•

5-15-51 r2

-,,15 693 2.6 2.7 15 .131" 1026 6.3 -. 73.81321 r- 96 13.6 13 oq 110o61321! 1596 23.2 23.8 195.01327 1914 37.3 3t_).2 300.0-1330 2196 66oO 67 358.31333 2526 109.9 -12.6 L 479.6

?1336 2,2 11•.7 134.9 535.51339 2196 34O5 65.9 3&'.013142 23)7 • 91.0 450.01345 190Q 35.7 36.6 2M .41314 1596 24.1 24.7 212o0

Calibration DatLŽ (First Aun)Flottorp Propeller

Nemeth LeadLng Edge .,*dification

5-16-51

0950 702 . -4 3.5 10.00933 1052 6.3 6.5 52.50936 1311 6.o 6.2 109.50939 1602 25.3 25.9 174.00942 1926 45.4 46.6 2%.00945 2199 74.8 76.8 331009 LO, 2397 98-3 101.0 L10o00951 2610 133.2 136.8 146.00954 2697 1t4,-o9 153.0 517o0 .0957 2199 72.4 74.4 3W40.01000 1314 :14o0 :4°4 114.0

KDC TR 52-190 3

AAFMC-147-WF-6.10-43-500 APPENDIX I (cont'd)

WHIRL TEST No...?335- .......

DEFLECTIONS

Time P . Actual (Corrected Torect L. E. I T.E.I Angle

Caqlibratior Data (Second htn)S.lotorop "Standardt1 ProJller

iDesigmn 1,o. 72A-hg6

5-16-51

J1450 7)41 3.1 5.2 30011"53 1002 L.5 li.6 h2.8114I56 1506 14i1 14 . 1• 100.514ý!59 1629 20.1 20.9 187.11502 167T 8 3.0 34.5 262.O

r!505 2190 63.5 &66.0 369-0150P 2400 8'9.3 92.8 432.01511 2610 121.9 126.6 50e.015U., 1926 55.7 51.1 283.01517 1(2•6 19.8 2o.6 192.5

"Calibration Data (Second Run) nFlottorp Propeller

Ne wth Leading Edge 1bdification

5-16-51

"1730 768 2.5 2.6 24,81755 999 5.1 5.2 57.1SIV-6 1533 15.°5 15o9 121.6

S1739 17o4 28.4 29.1 201.317•72 1704 26.8 28oO 201.3..17)5 1896 39.0 40.9 256.217W- 2190 70.5 73.7 3W 15

* 1751 2406 99.1 1035 L28.51754 2592 129.0 135.0 509-01757 2760 159.6 167.o 563.0

iWADC TR 52-190

TAi-LE 1

Sournd J~vol. at krSCOU`TO

it)..94 ILI6 96100 Xt9100

240)Dý 105 2357 1042 70) lo 67107

Le

0*0C

* 0

*:so

C..4

.0*P4

C..4

C4-.

IC

CCCto

R 5219

00.

004 i

000

00

0 0

Fr

f 41 -

000D

e AC R 2g9

S.:O

*00.

000

0O*4

rn

@ 55 UH

S.to

S..t

$4

i WAD TR 2-19

0* b

600

0O0

0

N4

cli

l~~jD' TR5219

0eS

S , 4

gee.S..

* S

* S

- - I-,,

*SSS.* 0

ICS�e 5-4

�I)r-1,-1

05-4

tl

5-ici.4-,to

5-40

4-,4-,0

ci

m

4-4

0

Q)r1

4-

4)

IC'

--'/

WADC TR 52-190 10

C..4

C0...

$.bP.f .

Cc

C.4.'

.4-.

C..d

* 0

f 0)

b0)

VIADC R 52-900)1

T77_ý7 1T 1 II 4-1 f'

T- 1 L i+. 41 4117

-- i 4 rT'ý4<

I... L +~~Hi ~ V iL L j1j4 1. .1 o'i ýJT 4 t 1-1~ - I t~~ 4 X fp- +--4~

-i -1 .r 4-t' iL IIs '- ft - rt1 V-I-' T1: -, 4-V z7 T

A1 4-11 H-.11 J1. H 4 '

T IiYf_ 4. -1

J-'-f -1~41 -it_ _ 4

¶ 4 .-4. r.

'A. 4_ T14

at frt + T,

ýTTv" 1 ±z I ~ i.t --pt!1 ~ -P t

V1 17 1 4-+ TJ.'1 4 41II

;TAr 4R 5 9

r~rrrrr Ir 42

2~~~~ F+jjj -~~{T'~-

r 4 4 J ,'-iýt~~r

Tti~ii~ 4K r~T -H~ Ht. b l _I t 1

4ý i

Ft 1- Z-

I~ x_

4-f4A

~~ 4: ±-,

t14

4, i-~ 1 F F; tV

±r1 rj4 ~ 4 p4 4 t ' it-114 r JH4 j 4-f

K 4I A-il IijTV 4t+.

I + L1$

ME[ #

1ý4

rT

HH: ot

T - iTJ_

-7 :ýT

+1714

Ul# H_ TT

#f- x

iff T T_

4#11t

I --f4

#4_44+fl_.H4+ U

A4+

01TIM1 :at

T 444-. +FP:q. 44++_PITn.-... TF 04

a [ji4. fjf,

4+1 44-ýI- S M_

Al.

NO - fIM

STE45 w lw_tt

41 H4rT

74 +",ýH

M -if

I L

-4LL

F 44-141

14 4

i4tftl LAU ST

T'

52-190

r H,ý 1U,4ý

qz a

+t- A I r ,ýv Aq+ 4H, -'4 4- -:Lý

J I

4- t1f,ý7. :1. T L

L i lm4ý1 Tt44VI i- -1 -- - , ý: -, -t"! , +

--tU iý 1,+1. cl+A 41!4 2 1

JI A

4 ri 1+,- ý4-. i t1+ LIt t T-,

4t4

.ý4 TTr

4: 4 LH +tV ;m ip 4- H7: , -- , .. - 1-4 ;-, 1,

A I t- j

4 t ýTA

1,441

L

t--! tJý tth-

I t-4 t

# NJ-11 o . - 1 .1 _;- ý; -,. _ _F_ " 1 444- -44 4 14 14-1- IF,44-

14414 4-f- fVT"T +

4 1 4,--4

4;ý q

I- L

+ r ýý, - ` 4.,

1 4-14:

T-r., r - Tý it ý 7ft.

f -1-1+

41 E7 TfrI oijliTI, +4ji

t -4 14 tI : IT !-Y,4,

.14 ý.4r4

#T -141 4

=L7ýt!!- . ± , ! ll,ý 1- 11 1 t ý ... 'i 1 4 r

ij 1-1 - - !I H1,

ý4

-

-ýi 7 1 i I ý, -

- -

I I:

T11 ll= 44 Ht4- I

L .-4 1 , I-L :,Lý ýti - 't ý: - I - - I L

10

44 +J+ -1 f +

IT -1 IXH-i.

#444 iý7(7-[444U,

41-T1-,T

471 H V

LLI4

+'44-1 t4-

+ ' H

4ý 4- :4ar#T 7TRill

TTttt 4

Iý 44- -H +H 7M Ifi--4" -

q. TL!

4 i 41 Lt

:r4 +1 Tf-

J-:L] -t.- - -14 -P4 - 1-T5P- a , I .-1 llj 4-141-

IT i

io.

4-4 A-1 14 47k:L vt j: tLtl ft-

r 1 -.T

t

+4-'

1+tT

ý4

-7 -7ý--

iF%.DC TR 52-190

4 H-- ~ ---- .¶ h .. .m -. T4-EB )* ~ -rt

~,1t- s~i~rntt4 I

+- 1- -

AH Tf~ + 1717j!~ jt t

1-r1 f4 41' t 4 Iii-4- 4 fi!~ 4A-vI

T4PI 44~r N

4q_ -f _ ¼ij i, 4$.. .H , r1~ :fm lF~t~

4,T iititF.:L 44 , - -- i4 I- I.' ; *~d1 1-

=4ll

A if

i4I- 4, ±

itf' H, M1 m,4

-~- :4 TV-

-;jj '1 <fltf1

i I-- r t

q: +4 4

*i'i rl +hT ~ j H I H tiit -i -

-4~~~ ---O--*

hl1 r- 4 r 4t

rT 4 I4t Tnt-4

TAij Tij. 40 19T

t t j 4 + l4'

DISTRiIBUTION LIST

Administration Office, Propeller LaboratoryjDirecborate of Laboratories, WCLBA - (1)

Aerodiynaaics Branch, Propeller LaboratoryDirectorate of Laboratories, WCLBY

ASTIA Docuncnt Service Center, DSC-SA- (2)

Publications and •rm.s Branch, Publishing Division

Air Adjutant General, WCAP - (1)

Director, Air University LibraryArTN: CR-3990Laxwell Air Force Base, Alabama

.eneth Aeronautical Laboratory

5241 Irving Park RoadChicago 41, Illinois

"K .,VDC TR 52-190 17

AAFMC- 147.WF-6-10-43-500

WHIRL TEST No...?55. ...............

I I I H'P" [ Thust DEFLECTIONSTie RC.o.P -Trreste REMARKS*

Time R.P.M. Actual Cor.c. ted Crrected L.E. I T. I Angie

C Ca 1ic xa -i on- 1)at a ( 'z,F~o'!•'oz'p ."tan,!r " - c-el r

: Design •fo. 72A-}4$

5-15-51

1315,7 •ir 693 2.6 2.7 15.g!31 1026 6.3 F 73-81321 12°96 13.6 13 o 110.o6

13214 1596 23,2 23 , 195.01327 1914 37Z3 .... 2 300o01330 2196 (x°; 07o6 358.31333 2526 109.9 112,6 47Q.°61556 2652 131.7 134.9 536.51339 2196 6%.3 65.9 368.013142 23M7 X' 910 45001345 1900 35.7 36.6 282.41314 1596 224.1 24.7 212 03

Calibration Data (First Run)Flottorp Propeller

Nemeth Leading Edge ),'dification

5-16-51

0930 702, 34 3.5 10.00933 1032 6.3 6.5 52.50936 1311 6,o 6.2 109.5C0939 1602 25.3 25.9 174.0091 1926 45.4 46.6 258.00945 2199 74.8 76-8 331o00910 2397 98-3 101.0 lao-O0951 2610 133.2 136.8 L06o00954 2697 lt4'o9 153.0 517o00957 2199 72.4 74.4 314.01000 1314 11"0 134,4 114.0

KADC TR 52-190 3

DISCLAIMER NOTICE

THIS DOCUMENT IS BEST QUALITY

PRACTICABLE. THE COPY FURNISHEDTO DDC CONTAINED A SIGNIFICANTNUMBER OF PAGES WHICH DO NOT

REPRODUCE LEGIBLY.

NOTICES

When Government drawings, specifications, or other data are usedfor any purpose other than in connection with a definitely related Govern-ment procurement operation, the United States Government thereby in-cursno responsibility nor any obligation whatsoever; and the fact thatthe Government may have formulated, furnished, or in any way suppliedthe said drawings, specifications, or other data, is not to be regardedby implication or otherwise as in any manner licensing the holder orany other person or corporation,or conveying any rights or permissionto manufacture, use, or sell any patented invention that may in anywaybe related thereto.

The information furnished herewith is made available for studyupon the understanding that the Government's proprietary interests inand relating thereto shall not be impaired. It is desired that the JudgeAdvocate (WCJ), Wright Air Development Center, Wright-PattersonAir Force Base, Ohio, be promptly notified of any apparent conflict be -tween the Government's proprietary interests and those of others.

mrneuemo

3i

WADC TECHNICAL REPORT 524190,

ELECTRIC MOTOR WHIRL TEST OF A FLOTTORP STANDARD TWO-BLADE PROPELLERAND A FLOTTORP STANDARD TWO-BLADE PROPELLER

INCORPORATING NEAETH MODIFIED LEADING EDGE

(Whirl Test No. ;2355)

Nathan ShowersPropeller Laboratory

Augu.u*t 1952

RDO No,.5874141

Wright Air Development CenterAir Research and Development Command

United StatesAir ForceWright-Patterson Air Force Base, Ohio

The test propellers unre submitted by Zeot Aeronauticallaboratory;, Chicago, Illinois, for electric mnotor vihirl testby 1fropeller labor atory, Aeron~autics Division, S~hr1t AirDeve1o1),--ent --6orjter. Thic test propallers were the propertyJof Flottorp >A uiactxuring C;o-.apony, Grand PRapidn, ihgnTie whrl test progra-m ,-.as co:-pleted on 15 and 16 thay 1951,under R~esearch andL -,,p;2ent Order "5i7JJJWP~ropellerAerodynatiic Analysis," Tirl AStIA& 23555.. Ian1athan Shoturs%was the project nncr

111111 ''1 .ADC TR 52-190

ABSTRAT

The electric motor whirl test of a Flottoro "stanlard" two blale,six ft. diametor, wood, fixed- pitch propeller was conjucteh Inelectric motor whirl test was then conducted on a similar "standard"?lottorp propeller that had been modified along the leading edce bythe Nemeth ý.eronautical Laboratory, Chicaro, Illinois. The modifica-tion cons stcd of a series of smooth injentations, in wave form, fromabout the 0.3 radius out to the tip of the blade. It was claimed byNe.eth Aeronautical Laboratory that sach modifications would increasethrust produced at any Civen horsepower and rpm condition.

Test data are presented coverinS static calibration of the twropropellers for comparative purposes. Calibration consisted of themeasurement of the values of the thrust produced and horsepoworabsorbed at various rpm. Results of the bests were inconclusive.

PBLICTITiON PEVIE7

This report has been reviewed and is approved.

Colonel, UChief, Propeller LaboratoryDirectorate of Laboratories

' ýADC TR 52-190 iii

• ..... Pa ge

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

Purpose of Test .. . . . . . . . . . . . . . . . . . . . . .. . .

Procedure of Test. . . . . . . 1

Test Results . . . . . . . . . . . . . . . . . . .. . . . . 2

Conclusions. . . . . . . . . . 2

Appendix i Calibration Dati. . ........... . . . . ... 3

Table 1 - Sound Level at Various rp, ........ . . .........

"Illustratioiis. . . . .is . . . .. ...........

Distribution List, ....................... ................ 17

...ADC TR 52-190 iv

ILLUSTR{ATIONS

Fig-ure Page

1 Front View r ottor;) Standard Frop•ller ........... 6

2 Front View Flottorp Standard Propeller lucor-poratingSNemetl- týodified Leading Edge . . ................... 7

3 Front View Close-Up of Blade - Flottor, StAarvnrd Propellor . 8

4 Front View Close-Tip of blade - FP).ttorn "'tnndard Propel1-rIncorporating flemeth MOodifie Lead.n, Edle ......... 9

Edge View of Blade - Flottorp Standard Propeller . . . . .. 10

6 Edge View of Blade - Flottorp Standprd PropellerIncorporating Nemeth 14odified Leadinf, Sge , . .-d ..... ii

7 Horsepower Curves for Flottorp PropellersWhirl Test No. 2355 (First Hun). . ... . . . . . . . . . . . . 12

8 Horsepower Curves for Flottorp Propeil-vrsArl Test No. 2355 (Second Run) . . .. . .... 13

S" Static Thrust Curves for Flottorn i~roneller,V hirl Test No. 2355 (First Run, . . . 1. . . l

10 Static Thrust Curves for Flottorp Prop•llersW',hirl Test Nlo. 235 (Seond .\un * . . 15...........

11 Sound Level Curves for Flottorp Pro-p 41 .rshnirl Test No. 2355 .. . . . . . . . . . 16

.{ 7;ADC TR 52-190 v

The 1i4c,ýth Aeronautical lef-oratory, in a perilod of t-im-e bef ore the ,,riting""o t:S rono haed. been- expo.Li~mnti-n,- -,;iit1 various desCILJO7s of procmeLler blades

iin an atte At. to Ln. rorovO ,)(rformancc ol' propellcrs.Toropoiettoconsste ofsvs raeruically reducin.- the leghOf the chlord ftebldsa

various slhatiors along,- the radius of the ILad - This aeawar od#egplanforrn to t'ne blade.

fN-nat.h Aec~ronlatical2 Th'txratory, :Lr conifemrnce IthPollorzborat'6orypea-onnel, did not .v any soilnd theoret~cal raoivfor the J.rmproverd.o~r for-.7no n l -7 eL o r this odiTf ica bi on, but pes c,- cc' Jat'a on, -~i %,ilrly

nodiledmoodel 'pie. rnthei-r -nn)," -wir ndesthhe 0o--!h eontical Laboratory concluded that- such', mndif:Lcat i ens J..tnl c c. ra Se t he thrustprodiuced at ancy rIiven horlseowur ond- r em conedition. TYhe fic aciliieof l'jetý'etlh Acronauttical laboratory pr-ohibited them fron A&In Lll scale

inet!'llninto the probicrai and t-hey appealcd to Propol-ler laboratory toMInduct the test of this report for them. 6iuf-ficient authoritative data wiere

nrcsrdc by o-et>, Aeronau-tical I;Vxoratorvy to. -Lnicnte t-hat conduh,,Ct of tilet'est uors uli e of advrn-ta-;e to teALIr Force.

PU YOSEd OF T.-EST

Thve -ryoreose of this test ins to obt~ain the static calibrat4ion character-istics OIL the Sublject pr opelle rs, t1-hus detel.-Aninfr tile rezlative value of theilAe~tl iqdifiications.

Thle "standard" i'lottorp propeller was of Deignlej. 72A-14?S, 6ierial. No.8&ý2-1. Thlle tiropel-lor was wood., six ft. diarmter, fixed pitch, with a taperedsquare tip planrifor-mi. Tho tip and outer siJx in. of the leading edg~e of theblade vý,ere protected by a rretal sheat~h. Thijs pro-peller is il-lustrated bFirgUres 1, 35, and 5.

The socond test propeller was a simiLlar Flott orp pro pel I cr that had beeninodif ied aogthe leadingir ed-e by Norieth Aeronautical laboratory. Thlemodifications consisted off a series of srooth indentations, in wvave form,f ovt ap;..roxinatoly the 0.3 radius Out to the tip of each blade,, This propel-ler had a tapered., round t'i- plexiform instead of the tapered square tip:lanform of the "standard" Flottorp propeller.. The tip. and1- outer six. in.of thre leadingý- edge of the blade -vwere protected by a mttal sheath. ThisIP'o-neller and the maodified leading edge are illustrated by Figre-, 2, 4., and'6.A No. 3745, 111 taper hub vvas used with bothpropellers.,

IMWCYDURE OF 'NO?

Thle subject propell ers vrerc inspected and assemabled in preparation for'M-hirl- testing. Thle v~jfrl test p-rogram consisted of thrust, horsepower and soundcalibrations at selected rpm. Calibration liirnits-vere 2800 rpm or th e start cFoýlade flutter,. whichever w-as reached first.

.iYiDC Tit 52-1901

T., 0l c212.. iiAoninn 'i' ;jmr. iv on3 w:cA r) -y C to assu;re t'h.t the :Yoctw (ls. Wz. t..ljd C.: o oba,-d 'IonC dat o te es

3 O C.L(2-J-7YUV .: -Li S Apeni 31. (icC:] j 'v. creted' ha o vesu

of ýi. prei0 %240 too th test1 prar ro0:lo no duf't

inforio t O a "5"Wa 4d ted ,011w. in thn~"'~ 2. ti..; of

110 -tor HMO

vlwUf 001.W 0 rwk.: ab23 ti currenitly* ICK_. JIUrIled to!,'f' a 1.:..02 H3:a- 3.; 7 Wyafl.~o.~ .. ~ si..1.2 tcoSts:.

.4 2 9 -2

A AFMC-1 47-WF-6-10.43- 500 APPENDIX I (contid)

WHIRL TEST No. 23----?.5........

Tm .PM.Corrected L. E.e T. E. A.9feTue . ctaH~'oreti P.utDFLCIN REMARKS-

Calihratior~ Data (Seconid hun)

Design 'ho 72A-h8

5-16-51

1/450 7)41 3.1 3.-2 3o014L53 102- 41.5 14.96 Lt2.81456 1350~ , 14 .4l 100.5214,Q 1629 20.1 20.9 187 .11502 18 76 5330 7,4.3 262.015-05 2190 63,5 6v3. o 369.o1500- 21400 9'5.3 92.8 432.01511 2 610 1211.a 326.6 509.01514- 1926 355.7 3-t.1 283.01517 1(-2 6 19Q.8 o. 192.5

Calibration Data (Second, Bum)Flottorp Propeller

Nenwth Ieadiing Edge !Ibdifi~cation

r-16-5

1730 769 2.5 2.6 24.91733 999 5.1. 5.2 57.1

"1739 1704 281.4 29.1 201.3.7L2 1704 26.8 20 2L.3.

1-745 3.896 39.0 40.9 256.2l 7b48 2190 70.5 73.7 3W42.51751. 2406 99.1. 103.5 L28051754 2592 129.0 1.35.0 509.01757- 2760 1159.61 167~o 563.0

iADC TR 52-1904

TAi3LE 1

S(Arnd Leval at, k-JoL us rpm'De 6 "eL)

ip lott orp, Ltaniard r p I llereth :.bdiiý'ied

1~494 1696n20 100 21o 10

24)105 237 1042703 LOW26 107

C -?o

, S... I. , 7

*°".

9o

9999

* So

'.9.d

.4.9

*4 9

099

9**H

*99 9

V%

" iif•• •,•I.C TR 52- 90 " .. .... 4

040

OW-

0000

4P0

o0-

F!00-

000D

WACT 2-9

IOee* I

p. ** 4 1*

e.g0**

OSOC

a..a..

C..

aa....

* S

* ae0eS..S.. S

'.4

a!

U 4,Co

0-pa 4,

I - 4/ 0I as

F f-I

I 0

C)4+q fD- S I0

(12

ntst t

01.4

hO{ 'rift.

'p -4IK WADO TR 52-190 1

-P-

0* b

0ee 0

M4C

0@oo

oOD 4)

.6.

P, 4-

P-4

0*0

*4D 5

* C•

290" S

* -Cs.I

f 0t,1-

,' • WDC TR52-19

0e*

.0O00

ILa..d

Sc

OSSn

Seeh.

*D .R5-101

S..4

I* b.

*s 5

0@0

*- 0

N.4

r-PIG-

0 -

'd

0 0

* 4)

bfl

TR~ 52-19

._L Lj T~ -4 '-4 ~ -t4 ~ ~ 4

1 -4 - p~4 ~~

-"4-4--' 4-4 4 -

-j

!4,i-rl i.

., "z'-- p. , I__ - I"

14 1ý -r ` 12 i < -±

4L

+"13 41- - - H1>1- +~

+ '44- 4ý

rtý14 _ A 1 -T i -~

--. '4. -HI- -l

4 41

17,L1

.4- ~ 4 4 -114

'~ CT! 2 9

tI

T-4t 1-r iljl

a nt'

Al ±4- H44i,

PTI T 'M t I

'Rw-4'

4- 4-

i4- ý7T7;- I

TiT,

tq

# fit..

+ , mi,

44-

, m"'Ifful*. .......... ta T

4 ýii4-ý+H4

+ 4j

it 4-

IRV

-W4

Hfý

FMvii: c 4ý,

4W

141 4

hi 'HI Mi - ±t44-

LE-ft 4 J7ý

+TH,

jL j-14 1 FFý

ittt A

T

Mtf

-7 -t J WO

Ttl t

iýý1 4- 4-

71

THIN. 4 #fý

+ +

1# 44Lt:ýT 144

t-;4

ýj j7

1, WiT -PA

-®r ri M,

44- +4 -4j

!L 4

-t: -1 M . Tl Hl",

IT 4-1 -H H -11; "-IT Hr 1 J. i.t" '#ý 4-tT I -tit Ilai0ni- .44 - L4: V J, 1-HT. r -,P 4414

TWMDG. TR 5ý-19Q

Hj'

777

id2T

44+

T,- #.

tV-4 J4 i4,

4

rr~~ fa J- . ....

~ ~WS

1-rn

IBM

H44

f-J -M 44

441 t:~~t~~____

_ Tit 52-19

-4414,

J 44"_TT T-1 :4H_ ma

_T41r4r

T_. T TT i- . I :___ , " f t 'ý7T + -14AL qil -,-j r

4 j i-Htl 4F T

tTý4ý4 LI J_ýý --LL

w +!j_ T 7r *ýtf I t+4-

H -7_L; MEIT Ll- T1

i-7f -T Tl- -4 41 t

-144, 4.L -114. 4_ -;4t I 1ý -t+I r4 i i

-4-j-4-11. it - i I * - pi

_T 1

+

7T'l4TH!

J_7

+ LIT M. ý P17"+

H+44

-A4 Fl-

,T ism!-

-r4- TT

4l.; VaTl_ 4,1

j +L rot 'i ;,T4 4-1.1T

All 77,",4-4.144

.1 44 14.,4 T Týv p "l,jj__ -7- FFF_4 , I I

Al

4,M t+ Or

4 i T;7: ..' L4-,. I . .... .... I _il

U 44 ..I I .... ITT

+4- -f+L

T I #1- 4

Lt:t+

11 4 -ý4

1. TTl Tr 4-5fl:t 'I--i iJ T

+-1 4144 f 4 14

4 __Tl+11

+

f +

ýM I K _1ýýt :144Mý I I V 3

T, --

.4_r I ' T-4 1 :' -11, ý .1 1 - . .... - - '..4 - , I . 1 11 -1. -,- _L , , I I

R A -ILT -- i+4A IML

-j-

t __ Ijjý_J

4- i+1

11W . T. L-I I

T4 4;Wr+_

44 +

14 +44i Wf I,

:Tk t 11, Lt. 74_týFTH iT

+

''7a- E. 7 It

I - t - -7 - rl-44

H:TH T

Mrm TlýPi

_LL Tj IV'T T

7 v ------ - ------T" '4

1-4 r -j 'Tl i-LLLaLj

!7ADC' TR: 5ý-199

DISTRIBUJTION1 LIST

Administration Office, Propeller LaboratoryDirectorate of Laboratories, YiCLBA - (1)

Aerodynamics Branch, Propeller LaboratoryDirectorate of Laboratories, UCLBY - (1)

ASTIA Document Service Center, DSC-SA - (2)

Publications and Forms Branch, Publishing Division 'Air Adjutant General, WCAPP-() 9

Director, Air University LibraryATT 1: CR-399ciLRaxvrell Air F'orce Base, Alabarma

Nemeth Aeronautical Laboratory'52Lhl Irving Park RoadChicag~o 414, Illinois

WA.DC TR 5290 17