NACA 302 Technical Report

7/30/2019 NACA 302 Technical Report

1/14

REPORT No. 302

FU LL SCALE TE STS ON A THIN METAL P ROP ELLE RAT VARIOU S TIP SP EE DS

By FRED E. WEXCKLangley MemoriaI Aeronautical Laboratory

463


2/14


3/14

REPORT No. 30.2FULL SCALE TESTS ON A THIN METALSPEEDS

PROPELLER AT VARIOUS PIT

BY FRED E. WEICK

SUMMARYlhh ~ epor t d escr i 6es an i nr es%i gat ion m ad e i n or der t o d et er m in e t he e$ect oj t ip speed on t he

cha ract er i st i cs of a i% .i n -b l aded meta l p ropelZer . 2_7i epr opel kr w ag m ou nt ed on a ~.i 3-7 ai Tpl an eunth a 180-EP. E2 engim , and tested i n the 20-foof propeller Teseamh twnei Oj tfie - i lTat ionalAdvi sor y i 70rnm i i t eef or Aeronaut i cs. I t um found that the e~ect of t i p speed m the pr opw lmceef i cien .z y was neg l igib le w it hin t he ~ a nge of t he t est%w hich w a s f rom 600 t o 1,000 jt . per see. (sh ou t0.6 to 0.9 the velocity of ~ound i n ai r). INTRODUCTION

T-bis know n tha t the nondimensiona l coeflicierks of thrust , pow er, a nd efficiency, in t ermsof w hich propeller cha ra ct erist ics a re usua lly expressed, va ry w it h size a nd speed; a nd t he sizea nd speed of a pr opeI Ier a re cnnvenient Iy represent ed by its tip speed in the pla ne of rot at ion.

Test s ha d been ma de previously on model propellers a t ~ a rious t ip speeds (references 1to 3) a nd ako on sma ll modeI a irfoils a t va rious a ir ~ elocit ies up to a nd beyond the velocity ofsound in a ir (references 4 a nd 5). The condit ions under which the a irfoil t est s were maderender t hem purely qua lit at ive in va lue, but t he result s of t he model propeller t est s a ppa rent lyha ve some q ua nt it at ,i~ e va lue. B oth set s of t est s indica t e a serious cha nge in coefficient s a tt he higher speeds, pa rt icula rly in rega rd t o a irfoil dra g coefficient s (w hich a re higher) a nd pro-peller efficiencies (w hich a re very much low er). These test s a .I sc indica te tha t t he effect ofhigh speed is less for thin tha n for thick sect ions, a nd, since a lI of t he sect ions used in theset est s w ere much thicker tha n tbe sect ions of modern met a l propellers, it ma y be inferred thstt he coefficien ts for t hin m et a l pr opeller s w ill be less a ff ect -ed by speed .

The invest iga tion described in this report is the fist t o obta in the effect of t ip speed on thecodficient s of a full-sca le thin-bIa ded met al propeller on a n actual a irpIa ne in a w ind tumaeLThe t ip speeds rea ched were not quit e a s high a s desira bIe, but represent the maximum ordi-n ar ily found in pr act ice. E ven t o obta in t hese t ip speeds, it w as necessa ry to set t he propeller ,w hich w as of the a djust a ble t ype, t o a n unusua Lly low pit ch. These t est s, therefore, a re t o bet a ken a s the fist st ep onIy in a more complet e invest iga tion on the efFect of t ip speeds w hich ish be made in the nea r futmre.

METHODS AND APPARATUSThe propeller used in t his invest iga tion w a s of t he det acha ble-bla de a huninum-a lI oy t ype,

ma de in a ccorda nce w ith Na vy dra wing No. 4413. (Fig. 1.) The t hickness ra tio of t he sect ionnea rest t he t ip ~ as 0.055 a nd tha t of t he sect ion a t 75 per cent of t he t ip ra dius w a s 0.078.The b~ a des w ere int ended for a propeI ler 9 ft . 6 i n. i n dia meter, but t he only hub a -ra iI a ble ~ a s1 inch short of t he st a nda rd length (it ha d been ma de so a s to sa ~ e w eight ), so tha t t he propeI lera s t est ed wa s a ctua lly 9 ft . 5 in . in diameter. k order t o obta in the highest pra ct ica ble t ipspeed w ith the power a va ila bIe, t he bla des were set a t t he compa ra t ively low bla de a ngle of7a t t he 42 i n . radius . This , of course, result ed in a propeHer of low er pit ch tha n is found inpra ct ice, but ha d the compensa ting a d-ra nt a ge tha t a ny t ip speed effect w ould be exa ggera tedbeca use of t he low pit ch.

465


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466 REPORT NATIANAL ADVISORY COMMIfiEE FOR AERONAUTICSThe t est s w ere ma de in t he pr opeI Ier resea rch t unnel of t he NT&t iona IAdvisory C ommit tee

for Aerona ut ics, w hich ha s a n open jet-a ir st rea m 20 ft . in dia meter ca pa ble of velocit ies up to110 M. P . H . A complete descript ion of the tunnel, ba la nces, a nd other mea sur ing a ppa ra tusis given in reference 6.

A Vought VE7 a irpla ne w ith a Wright E2, 180 HP . engine, w hich ha d been mounted int ihe t unnel for a not her invest iga tion (reference 7), was a lso used for these t est s. S ince theVE-7 a irpla ne ha s a spa n of 34 ft ., t he w ings projected a bout 7 ft . out side of the a ir st ream.Figure 2 i s a photogra ph of the a irpla ne in the experiment chamber. I t is considered tha t a

CFIG.1.Metal propeller blade 9.5feet in diameter. Right hard. X-o.4413ORDINATES OF SECTIO&-S AT VARIOUS R.4DII FOR EXPERIhfENT.4L METAL PROPELLER BLADE

9.5 ft. diameter, right-band (fig. 1)I 10r I 12 rs 1pperI2.5. .-- . . . . . . . . . . . . . . . . . . . . . . .5. . . . . . . . . . ..- . . ..-.. -.-... -..-1lo-. . . . . . . . . . . . . . . . . . . . . . . . .20. . . . . . . . . . . . . . . . . . . . . . . . ----- [30. . ---. . - .----. . --. ---. . ------40-----------------------------5 0 - . . . . . . . . . . . . . . . . . . . . . . . . . . . .60. . ..-.. --.-- . . . . . . ..--. -.-.-17 0 - . . . . . . . . . . . . . . . . . . . . . . . . . . . .w-- .. . .. . -------------------93--. .---. . . . . . . . . . . . . . . . . . . . . I_1

,?0.62i:L 45l.%L 561.ML 381.17.89.55

Lower I Upper,) ,/0.28 0.68.44.59 1:E.70 1.39.74 1.46.73 1.45.70 1.39.04 L 27.55 1.08.42 .82.26 .51.

Lowert,0.14.21.28.33.35.35.33.80.26.20.12

Rad. T. E--------------------- 0.21 I 0.16Rad. L. E__ . . . . . . . ..-. .-_.. .72 .31ICho rd . . . . . . . . . . . . . . . . . . . . . . . 6.55 6.64 -

18r ~t, ~Upper Upper

/, /10:;: 0.39.55.94 .751.13 .K1L 19 .951.M .941.13L 04 ::.88 .70.67 .53.42 .330.03 0.07.12 .10 7.46 7.6!3

3W rUpper

/,0.32.46.61.73.77.;;:67.57.43.270.05.087.55

t

,, ,/0.26 0.20.37 .2s.50 .38.60 .46.63 .48.62. .48.46.:; .42,47 .36.35 .27.22 .17l

0.05 0.04.06 .05

YIT

48 rUpwr

,,0.14.21.27.32.34.34.32.30.23.19.120.03.0+34.02

54 rUpper

,,0.02.08.11.15.18.19.19.18.17.14.110::!3.49

The chord is divided into 10equal parts , orstations, with the one at the leadhg edgesubdivided into halves and quarters, S equals stationsin per sent ofchord from the leading edge.sufficient port ion of the a irpla ne w as in the a ir st rea m to include a II pa rt s w hich w ould rea ct onor be influenced by t he pr opeller .

In order t o det ermine t he pit ch of t he propeI Ier in opera tion, the deflect ion of one bla de w asmea sured a t the 42 i n, ra dius, by mea ns of a t elescope mount ed on a gra dua ted ba se a nd sight edon first the lea ding a nd t hen t he t ra ihng edge. This w as done w hile the propeller w as st andingst ill a nd t hen w as repea ted for ea ch t est point w hile t he propeller w as running.

The a ir veIocit y w as obta ined by mea ns of ca libra ted st a tic pla tes in the return pa ssa ges,lea ding t o a ma nomet er in t he experiment cha mber. The revolut ion speed of t he propeller w a sr ea d dir ect Iy from a specia lly built a nd ca libra ted E Igin chronomet ric t achomet er.


5/14

FULL SCALE TESTS ON A THIN METAL PROPELLER 467The VIG7, a s mounted in the tunnel, ha d complet ely enclosed w ithin it a specia I st ee~

skeIetcm fusela ge w ith a built -in dynamometer t o mea sure the engine a nd propeller t orquedirect Iy. (Reference 6.) An observer sa t in the rea r cockpit of the a irpla ne throughout thet est s t o opera te t he engine a nd rea d t he torque sca le a nd the t achomet er .

The re.sdt anfi horizonta l force of t he propeller-body combina tion, -w hich ma y be eit hera t hr ust or a dra g, w a s mea sured on t he reguI ar t hr ust ba Ia nce (a Isa described in reference 6).This result a nfi horizont a l force R may be thought of a s composed of three horizont a lcomponen ts, such t ha t l ?= T -D -AD,where T= t he thrust of t he propeller while opera t ing in front of t he body (the tension in

t he cr an k sh aft ).D = the dra g of the a irpIa ne a lone (w ithout propeller) a t t he same a ir veIocit y a nd

density.AD= t he increa se in dra g of t he a irpla ne w -it h propeller , due to the slip shrea m.

~G. Z.%W-iairplane mounted in propeller resef$mhtunneII n or der t o obt a in t he pr opulsive e%kien cy , w hich in cludes t he pr opelI er -body in ter fer en ce,

a n effect ive t hrust i is used w hich is defined a sE ffect ive t hrust = T AD = E + D.

RESULTSThe result s of t he test s a re given in Figures 3 to 7, inclusive, a nd in Ta bles Y a nd 11. They

a re reduced t o t he usua l coefficient s of t hrust , pow er, a nd propulsive efbiency,~ ~ = E ffect ive t hrust

pn2D~~ P = I nput pow er

pn3Ds~ = E ffect ive t hrust X velocit y of a dva nce

I nput pow erwhere D = propeller dia meter a nd n = revolut ions per unit t ime. S ince the coefficient s a re di-rnent ionless, a ny homogeneous syst em of unit s ma y be used.


6/14

468 REPORT N.4 TIONAIJ ADVISORY COMMITTEE TOR AERONAUTICS

nBFIG.3.Propel Ier 4413. (7 at 42) ORVE-7 airplane. 1,200R . P. i lf.Tipspeed=591 [t./sec. V/c=O.526

,nDFIG. 5.Prope] ler 4413 . (7 at 42~ on VE-7 airplane. l,fXOR. P. M.Tipspeed=788 ft./see. V/c=O.702

.06L7 v,#-x */

.050

.040

.030 r&%&.020

0,-

7 0/00 Jo .20 .30 .40 ,50 2vFIG.4.Propeller 4413. (7 at 42) on VE-7 airplane. 1,400 R. P. MTipsNed=6fQ ft./see. T7c=0.Ll14

.060

.050

.040

.030d%Q .020 ,

.Ofo

-.O[OO ./0 .20 . .?0 .40 .50vniaFIG. 6.Pr0pe]ler 441% (7 at42}on T7E-7 airpkne. l,&M~Ff~P.. M.Tipspeed=&S7 ft.,kec. V/c=O.791.


7/14

FULL SCALE TESTS Oh A THIN METAL PROPELLER 469The a nguIa r deflect ions a t fihe 42 in. ra dius, w hich w ere mea sured for ea ch test poinh, a re

a lso pIot t ed in Figures 3 to 7. lr t genera l, t he deflect ion wa s very smaLl a t the va lues of~ nea r ma ximum efficiency , but a t higher a nd Iower va Iues of,: t here w a s a n ~ crea se ~ thebla de a ngle, which w as grea t er for the higher rot a t iona l speeds th~ for the lower ones.

A compa r ison of the thrust coefficient s obt a ined a t t he va rious rot a t iona l speeds (or t ipspeeds) is given in Figure 8, a nd a compa rison of the power co~ cient s ~ Fig~ e 9. IL ~ flbe not iced tha t pa rt icula rly a t t he low va lues of ~ ? the thrust a nd pow er coefficient s increa sew it h a n increa se in t ip speed. This ca n be ent irely a ccount ed for by t he deflect ion of the bla desin opera tion, so a ppa rent ly is not due t o sca le or compr essibili.ky effect t o a n a ppr ecia ble ext ent .

The efficiencies found a t t he va rious t ip speeds a re pIot t ed a ga insi ~ - iu F ia gwe 10. Thecurves for a ll t ip speeds a re &hesa me w it hin t he limit s of a ccura cy of t he exper iment s, indica ting

.0/0

/ i Qt ii\ I

1 IR%]IT \ \ !i i: \tpJ.3f:\~ t. II11--l-All 1 I o 0v

nmFuI. 7.Pro@lM 4413. (i at 42? on VE-7 8irpIfme. 2,033 R. P. M.Tip speed=%% ft.[see. VIC=O.SZ3

tha t t he effect of t ip speed on eficie~ cy is negligible for this pa rt icula r ihin-bla ded mekd pro-peI Ier w it hin the ra nge of t ip speeds t est ed (from a bout 0.5 t o 0.92 t he veIociLy of sound in a ir).

ln Figure I I t he efficiencies a nd va lues of ~ a re plot t ed a ga inst the fa cfior

Th is is a form of speed -pow er coefficient w hich r epr esen ts t he r eq uir ed per forma nce of a pr opelleron a n a ir pI ane, since it incI udes t he pow er fibsorbed, t he revolut ions, a nd t he velocit y of a dva nce.P ropellers opera ting a t t he sa me due of this coefficient a re therefore -ivort ing under simila rrequirement s, a nd hence a compa rison of ef15ciencies ca n be ma de on a fa ir ba sis. F igure 11show s cl~ a rly t ha t from the st andpoint of effect i~ eness of opera tion on a n a irpla ne, the t ip speedis of no pra ct ica l import ance w it kin t he limit s of t hese experiment s.


8/14

470 REPORT NATIONAL ADVISORY

.0601 $ I1600 R.Rh%

.050L; \~

Fm . 10.Propeller 4413. (7 at 42) on VE-7 airplane. 1,200,1,400, I,6@ l,W, and 2,cHY.3. P. M. Tfp speeds, 591to 9S6It./see.

C!OMMI-TE E FOR AERONAUT ICS.0/6

\ . ---\.0/4 -! I I

/400, / 2000.0/2

.010

.008Cp.am

\

.004

.002

0 Jo .20 ,30 .40 .50vmDFIG.9.Propeller 4413, (7at 4Y)on VE-7 sfrpkme

/.0 .50

.8 / HY .40H 5A

.6. fi .

.30v vFD.4 / .20

/ I.2 ~ /

I

o .2 .4 .6 .8 10F5pvp>

FIG. Il.Propeller 4413. (7at 42) on VE-7 airplane. l,!XO,1,.4(M,,KM,I,&Xl,and 2,c03R, P, M. Tip speeds, 59I to gs6ft,/so~,


9/14

FULIJ SCALE TESTS Oh A THIN METAL PROPELLER 471CONCLUSION

The effect of t ip speed on t he efikieney a nd performa nce coefficient s of t he propelI er t est edvm.s negligible throughout the ra nge of the t est s, except a s the thrust a nd pow er coefficient sw ere a ffect ed by the slight cha nge of pit ch due to defect ion. Appa rent ly the coefficient s w erenot a ffected by sca Ie or compressibfity to a n a pprecia ble ext ent .

LANGLEY &f EMOE IAL lLE ROXAUTICAL LABORATORY,NATIONAL ADVISORY COMMITTEE F OR AERONAUTICS,

LANGLEY F IE LD, V~. , J une W, 1928.


10/14

REFERENCESReference 1. Douglass, G. P., and Wood, R. McKinnon: The Effects of Tip Speed on Airscrew Performance,

An Experimental Investigation of the Performance of an Airscrew over a Range of Speeds of Revolutionfrom Model Speeds up to Tip Speeds in Excess of the ~elocity of Sound in Air, British A. R, C. Reportsand Memoranda No. 884, 1923.

Reference 2. Douglass, G. P., and Perring, W. G. A.: Wind Tunnel Tests with High Tip Speed Airscrews.The Characteristics of the Airfoil Section R. A. F. 31a at High Speeds. British A. R. C. Reports andMemoranda No. 1086, 1927,

Reference 3. Douglass, G. P., and Perring, W. G. A.: NTind Tunnel Tests with Eigh Tip Speed Airserews.The Characteristics of a Bi-corwex Airfoil at High Speeds. British A. R. C, Reports and MemorandaNO. 1091, 1927.

Reference 4. Briggs, L. J., Hull, G. F., and Dryden, H. L.: The Aerodynamic Characteristics of ~~rfoik. atHigh Speeds. N. A. C. A. Technical Report No. 207, 1925.Reference 5. Briggs, L. J., and Dryden, H. L.: Pressure Distribution over Airfoils at High Speeds. N, A. C. A.Technical Report No. 225, 1927.Reference 6. Weick, Fred E., and Wood, DonaId H.: The Twenty-Foot Propeller Research Tunnel of theiNational Advisory Committee for Aeronautics. N. A. C. A. TechnicaI Report No. 300, 1928,Reference 7. Weick, Fred E.: Full Scale Tests of Wood Propellers on a VE-7 Airplane in the PropeIler ResearchTunneL N. A. C. A. Technical Report No. 301, 192S.472


11/14

FUjJ L SCALE TESTS OX A THEYTABLE I

TEST DATAPr Op elIe r No . 4 41 37

1 ,2 0 0 R. P. %1 .(T ip s p ee d . 59 1 .7 ft . ~s e c. )

METAL PROPELLER

at 42 in.*

p ;:::+%*;,,::[::8:.002365002365002365~ -,,

58:2 I i ;:8 26 .00336 :00719 . +&k .20s :0002365 58.2 1,235 85 : 22 .00281 .00730 .442 .170002364 .2543 ! 1,205 *8 : 00577 .00794 .423002364 87 ~ ;; : .3:7:: ; ! 1, 195 .200520 .00800 .424 .2{6 .0002378 \ 1,220 152 ~ 317 .0414 .0133 . 0S25 .257 3002378 10:7 q 1,220 152 } 317 , .0414 .0133 . 0S25 .257.00234 1:0H. 65 1,205 149 t 311 .0424 .01356 .0905 .284 .700234 11.65 1, 205 149 ~ 307 . 041s002378 .01350 .0905 -281 .639.2 1, 210 121 1 15s .0210002378

.01078 .304 .591 .439.2 1,210 124 1 159 .0211 .01104 .304 .581 .0002375 43.8 1, 215 115 122 .01605 ; :~1: . 33s -535 .3.002375 115 122 ,.002369 I ::: ~~?:: .01605 . 33s .535 .3:O& ~ 101 ; . 013s .00954 . 35s .519 .1002369 45.6 ~ 1, 195 101002369 .0138 .00961 . 35s 514 .138.4 i 1>200 123 160 . 021T .01118 .300 : 5s2 o002369 3S. 2 i 1, 195 l~o 157 I .0214 .01096.002367 32.0 1, 165 .300 . 5S6 :2123 1s0 ~ . 025S .0118 258 .563.002367 .132.0 1, 155 120 174 , .0254 .01174 :2605 .563 .1

1,=$00R. P. M.(Tip speed 690.3 ft.[see.)

O.002365 6S. 4 1, 410 104 14 0. 0013s O.00687 0.453 0.0912 t +0. 4.002365 68.2 1,415 106 00695 .451 0S25;: : %+3: : .3.00237 67.1 1, 400 106 00707 .449 :1265 .5.00237 66.8 1, 395 105.002365 .0019 .00705 .449 .12164.9 1, 410 116 :; .00461 .00765 .432 .260 .:.002365 649 1,405 113 42 .00415 .00747 .433 .241 4.002365 [ 59.3 1, 395 131 90.002365 .00900 . 008S3 .399 .406 I ;459.3 1,385 127 .00915 . 00S52.002362 .402 .4321:: 355.4 I, 425 152 .0134 . 009s3 .365 .496 .7.002362 55.4 1,425 151 137.002378 0132 .00973 ; .36.5 .49413.6 I, 405 207 430-5 :0424 .01364 ~ .0909 .283 ;. (302378 13-6 1,405 206 434.5 .0429 .01360 I .0909 .287.00234 13.25 1:11, 405 20+ 427 .0428 .0137 ! . 0ss2 274 ..00234 13.25 1,405 205 422 . OQ*.002380 .01374 . 0ss2 :27238.3 1: ;1, 375 175 255 .0262 . :;::: I . ;::; .569 . 1.002380 38.3 1, 375 173 252 .0259.002375 40.9 1, 425 175 229.002375 .021944.2 [ 1, 420 175 224 I 01127 f ; 29550113 I ,.292 : :;:

::.002369 i : EIN :01066 .307 .245.8 1, 400 160 200.002369 45.8 1, 38.5 160 :% 7. 1197.002369 .0200 .01085 .310 .572 . 139.1 1, 365 175 253 .0264 .01229 .269 .578.002369 38.7 1,375 170 246 .0254 .01172 .264 .572 . ;.002367 32.9 1, 400 187 297.002367 .0296 .01250 .2205 FJ232.9 1, 390 185 295 . 029S +. 1I 01252 .222 : 528 . 2

.


12/14

474 REPORT NATIONAL .4D%ISORY COMMITTEE F OR AERON.4 UTICSTABLE IContinued

TEST D.A,TAContinued1,600 R. P. M.

(Tip speecl 78S.9 fc.~sec.)I V \ NP ;M.P. H. ~R. P. M Def. ato 42 in.Rad,, cleg,Qlb. ft.

0.00238 f 83.8. 0023S 83.8.002365 78.3.002365 ; 78.4.002365 71.9.002365 70. i.002365 69.6.002365- t ;;;: ~%~5 [ 67.7; 63.7.002365 ; 65.0.002365 ; 60.1.002365.002362 ! ~~ ;.002362 56.1 ..022378 14.9.002378 14.9. 00Q342 15.25

10610213313315815816716417717719218S19919720s207267269264257267269235234223222240238248243

62 j O. 004S5. ~ O.0056 6! ~ . 0054~. .0054. . i. 00678a 49s.500458:458, 422.415.411

-0.432. 506.0155:.0224. 30s. 31s.353.342 ,A& ~: p6 [:530 ~.552 !.540.275.273.281 ,.300 .546 ~.541, .56s ;.567 I.576.578 ~.547 ;.552.520 ~.516 [

+2. 42.07::.4::.3.19-.5.5.5.:.;81:71.1.. 2

7::.2.17: ;.2.1

4; . i77 , . oo593__;81 ~ .00622 ,96 ~ . 00745:..,91 1 . Qa~nz_...127 -.127174 : :0133::153 .011619!3 .0152199 .0152 ~_233 .0179226 .0175 :561 .0426560 . 042s ::551 .0432.533 .08201, 8251, 8101, 8051, 7651, 7501, 7951, 7951, 7951, 7851, 8001! 795

1871851521491521532182172232282462442492512662632782752812773763773603593333313083053003003163M341342

45.5 0.0027847 . 00289K

0.0076 : 0.446.0076 /

O.163.449. 4s5.488.491.491.411.410.387379_.371.370360_.360.337.336318..322.202.302.0919.0919.0947.0967.213212:229.229

.171. 278. 298. 343. 341.346.342.435.475.490.477.519.514.554.550.554.562.570.570

.282.284.291.299.529.530.538.542.561.558.523.527488:478

58617171123120168191

. 00350... 00372. 00420. oo417-.00733 -.00727.01053.01220.01320.01280.01455.0147.01768.0175. 01!34 .,. .,..0444 _: :::; :.0442.0333.0330. g::.0283.0282.0330.03300356-:0357

I

I

1217211240240293

.00237 -.00237.002365.002365.002365.002365.002362.002362

.002378

.3

.:.61: ?.:.9.981:0.0.1. ;:1,.0

+: :.. 2

. 00237S.002342.002342.002380.002378.002375.002375.002365.002365.002371.002371

I} .01432 I.01335.01320.01270.012681:8051, 7801, 7701, 7751, 7751, 7651, 7.751, 8101, 805

.01245 1 .247 i:M i.2085186:1836 I

.01245.01325.01308.01356.0137

I534598597.002367.002367 I 1


13/14

FULL SC.4LE TESTS Ox A THIN - 3 XETAIJ PROPELLERTABLE ICo nt in u ed

T EST DAT .&-Co n t in u e d2,000R. P. M.

[Tip s pe ed 9 S6 .1 ft .~s ec .)

TIb..

De f. a tCP V/nD 7 42 in.Rad., deg.x QR.P. M. lb. ft.[

vIL P. H.

0.0093 /L00922 0.401.402.444.440.454.454.371.371.345 ,:%: ~.:;; ~.4327 I.3~5.304 ~.292.290 \.;::;]20151:1985.212.214.223,.221:-~941.191 ,---

:M

o.39s +2. .2. 3s5 2.1. MO L 7.190 L6.0754 L 7.0695 1: ;.468.470 .4.523 .4. 52S.535 .:.526 .s.564 .5564 --. 31s 1::

0. 0023S. 0023S. oo~365.002365.00236

85. s85. S94.194.196.196.0so. Iso- 173.274.372.172. 169.570.065.765.562-261220.222.443.042.545.645.747.747.741.140.337.13&7.

2s528224023S217215312314323321351360339345361361371373440451431433422424405417

190181696924222642663283273763S239739s45745s4s0$90S9S941735748711711671679735735750755

. 00ss1.00336.00334.001194.001102

-. :p; I.0078 ~.0072.0072 ~.0100201009:01072. 0105s ~.01139 I

.00236.002365.002365.002365.002365.01263.01272.01625.01605. 01s2002365.002365. ()()237.00237.002365

. oo~365.002365.002365. oo~342. ooz342. 0023S. o023s.002376. ooz376. @3~37

. 01s05.01940194-0220

.0221

..0140.01403.01363.01373.0132.0135. 013s. 013S2.01410.01410

.513 --------.511 .4. ~32. a31 .;.:51 .0335: 51_2 .:. 5~2.480 .;. 47s .2

.00237.002369

.002369.0Q2367.002367. 0~63. 03s1. 03s4

FIX.&LTABLE II

ADTGSTED COEFFICIENTSPrope lIe r No- 4 41 37 a t 4 2 in . Ra d .1,200 R. P. M.

(Tip speed 591.7 ft./see.)v CTnD ICp+-l :~2~~4.0135 ..0132 .419 :0760 :356.0127 .504 . 15s .479.0120 .560 . 2S6 .607-- .470 .740: l% : g;; 1 - S79.0086 .379 i % 1.035.0070 .103 L 622 ; 1.214

0-0409.0369.0321.0269.. 0211.0142. 00s15.0016

0.10.15.20.25. %.40.45

1,400 R. P. M.(Tip speed 690.3 ft.~sec.)

0.10.x.25.30. M.45

0-0415.03725.0325.0271.0211.0150. 00S6.001.5

0.0136 0.305.420.503.560.575.525.396.0965

0.0271. 075s.1576.284.4707251:086L 622

0.234.0133.0129.0121.0110.0100. 00s7.0070

.356.476.604.739S801:0351.213


14/14

476 REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICSTABLE IiCo n t in u ed

F INAL ADJ US TED COE FF ICI1 3 NTS -Co n tin u ed1,600 R. P. M.

(Tip speed 788.9 ft./see.)

Cp

O.0138.013.5.0129.0122.0113.0101.0089.0072

0.10. i :.25.::.40.45

0.0421.0380.0330.0274.0215: %%.0018

0. x);: %.571.530.396:1125

0.02696.0751.1575. 2&5.464.7211.071L 601

0.234.356.479.605.735i W;1.207I . .

1,800 R. P-. M.(Tip speed 887.5 ft. fsec.)

f O.026.35.0737.1550.2785.4597091:0521.570

0.10.15.20.25.30. xl.45

0.0438.0392.03390.01445,0140

.0281.0220.0158.0093.00245 .0075 I2,000 R. PnM.

(Tip speed 986.1 ft.~sec.)0.0151.0146

. ..0.30$-:%.561.570.518388:1154

.0139.0130.0119.0106.0092.00740019 f

NACA 302 Technical Report

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