NASA Tests on 13 Navy Type Model Propellers

8/17/2019 NASA Tests on 13 Navy Type Model Propellers

1/15

REPORT No.237

TESTS ON THIRTEEN NAVY TYPE IMODEL

PROPELLERS

By W. F. I URAND

Stanford University

-Q4SS—27—11

151


2/15


3/15

REPORT No. 237

TESTS 01’THIRTEEN NAVY TYPE MODEL

B y W. F. DURMD

PROPELLERS

P U RP OS E OF TE S T

Th e t est s on th esem odelpr opeH er sw erecon duct eda t St a nfor dL ~ n ivers;t ym derr esea rch

a ut horiza tion of t he Na tiona l Adt iory C ommit t ee for Aerona ut ics a nd w ere undert a ken for

t he pur pos e of det erm in in g t he per for ma nce coefficien ts a nd ch ar act er ist ics for cer ta in select ed

ser ies of propellers of form a nd Q-pe a s commonly used in recent s~ avy designs.

The first ser ies includes seven propellers of pit ch ra tio ~ a rying by 0.10 from 0.50 t o 1.10,

t he a rea , form of bla de, t h ickness, et c.

ha d show n good resulk.

, represent ing a n a rbit ra ry st a nda rd propeLler w hich

The second series covers cha nges in t hickness of bla de sect ion, ot her t hings eq ua l, a nd t he

t h ird ser ies, cha nges in bla de a rea , ot her t hings equa l.

These models a re a ll of t he st a nda rd 36-inch dia met er employed in t his la bora tory .

The dimensions of t hese model forms a re a s show n in F igures 1 t o 14.

It -dl be not iced t ha t propellers A t o G form t he ser ies on pit ch ra t io, C , N, 1, J t he

ser ies on t hickness of sect ion, a nd K , M, C , L t he ser ies on a rea .

ME TH OD OF TES T

The me~ h ods follow ed iu t hese t est s w ere simila r t o t hose of like t est s preciously report ed,

a nd need not be more pa rt icul~ r ly descr ibed h ere.

RESULTS

The result s a re present ed in t a bula r a nd ma uhka l form a s follow s:

Th e d-y na m ic w in d pr es su re

pP 2 in

poun ds per sq ua re foot .

The w ind velocit y in feet per second V.

Th e r e-r oI ut ion s per m in ut e (A9.

Th e w due of t he slip funct ion T “/ n D .

The t hrust in pounds (T’).

The t orq ue in foot -pounds (Q) from m chja re ca kda ted

Ta b ula r result s.~ ln Ta ble I a re given t h; okerved va lues for t he folIow -iuu q ua nt it ies:

((l)

(5)

(c)

(d)

(e,)

(f)

(g)

(?L )

(j )

I n a ddit ion, in Ta ble 11 a re given, & derh-ed

a mo~ ~ t he observed point s, va lues of t he follow ing:

(a ) The t hrust coef. ~ -,.

?’a Iues of t he t hrust coef. C T= p~ 4s

Va lu es of t he po-w er coef. C P , = P &s

Va lues of t he po= er coef. C ’p, = &.

Va lues of t he pow er coef. C ., = ~ z.

from smoot h curves dra w n t hrough a w l

(b) T he pow er coef. A,”

(c) Th e efficien cy q .

153


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154

REPORT NATIONAL .4DVISORY COMMITTEE FOR AERONAUTICS

G ra ph ica l resu 7t s.—I n F igu res 15t 027 a resh ow n for ea ch pr opeller t hefollow in g:

m

(a ) Theobserved point s for t het hrust coef. ~ ~ i.

(b) Th eobs er ved poin ts for th epow er c oef.---&j.

(c) The smoot h curve t hrough a nd a mong t he point s of (a ) a nd giving t he a djust ed

or most proba ble va lues a sin Ta ble I I .

(d) Thesmoot h curve t hrough a nda mon gt he poin t sof (b) a ndgi~ ing t he a djust ed

or most proba ble va lues as in Ta ble H .

(e) The curve of va lues of t he efficiency ~ a s deri-red from t he va lue of t he coefficient s

of t hrust a nd pow er , a s in Ta ble I L

D M X J S S I O N

The slip funct ion T~ /nD is ot herw ise (V/n) + D a nd t his is t he ra t io of t he a dva nce per

revolut ion t o t he dia met er , I f t he propeller bla de consist ed simply of a n idea lly t hin t rue

helicoida l surfa ce screw ing t hrough t he a ir w it hout slip or a ct ion on t he a ir , t he a dva nce

per revolut ion w ould be equa l t o t he pit ch of t he helicoida l surfa ce. I n such ca se t here w ould

be developed, of course, no t hrust on or by t he propeller. I n a n a ct ua l propeller t he a dva nce

per re~ olut ion w hich produces no t hrust gives a n eq uiva lent or vir t ua l pit ch a nd t he ra tio of

t h is t o dia met er gives a form of eq uiva lent or virt ua l pit ch ra tio. This w ill obviously give n

point on t he a xis of V/nD w here t he t hrust is zero a nd w ill t hus furr iish one limit of t he w rious

performa nce curves for t he propeller .

The ot her limit w ill likew ise be founcl a t t he poin t

w here V/nD = O or w here t he speed of a dya nce T7= O.

Turning t o t he va hes a s given in t he t a bles a nd figures, it is seen t ha t in a ll ca ses t he va lue

of

V/ n D

for T’= O k grea ter t ha n t he nomina l or fa ce pit ch ra tio, a nd in conseq uence t he va lue

of t he vir t ua l pit ch ba sed on a dva nce for

T = O is

in a ll ca ses grea ter t ha n t he fa ce or nomina l

pit ch. This is, of course, a w ell-know n cha ra ct er ist ic of a ct ua l propellers result ing from t he

a erodyna mic propert ies of t he st anda rd form of propeller sect ion w it h a pra ct ica lly pla ne clr i~ -

ing fa ce a nd a definit ely rounded ba ck.

The a mount of increa se in pit ch, a s indica t ed by t he

va lue of

V/ n D

for

T =

O a s compa red w it h t he nomina l pit ch ra tio, is seen in genera l t o be of t he

order of 20 t o 40 per cent , t he increa se being grea ter for t hick bla des t ha n for t hin, a s w ould

n a tu ra lly be expect ed .

Th e gen era l ch ara ct er of t he coefficient s C T, OP ,, a nd of t he efficiency ~ is pla inly sh ow -n by

t he dia gra ms, F igures 15 t o 27.

The coefih ient Or begins on t he a xis of

V/ n D

a t t he point

for

T = O

a nd rises sloping t o t he left , nea rly st ra ight a t first a nd t hen curving over more defi-

nit ely t o some fina l limit va lue for

T 7/ n D= O.

The coefficient C P , st ar t s w it h a definit e va lue

for t he

V/ n D

va lue w hich gives

T =

O a nd rises a t first st eeply a nd t hen curves more a nd more

definit ely t ow ard t he horizont a l unt il over t he w orking ra nge of t he propeller it is oft en nea rly

horizont a l. I n genera l, fur t hermore, t hese curves rea ch a ma ximum va lue for some sma ll

va lue of T 7/ n D a nd t hen droop slight ly t o t he t ermina l va lue for T7/ nD= O.

The curve of v begins, of course, a t O w here

T = O on

t he r ight a nd ends a t O w here V=

d (

V/ nD =

O) on t he left . I t r ises, a t first ra pidly , t o a ma ximum usua lly a t a va lue of

T ’/ n D

nea r or somew ha t less t ha n t ha t equa l t o t he nomina l pit ch ra tio, a nd t hence it declines more

gra dua lly t o t he origin w here V= O.

C ompa ring now t he va lues for t he propellers A t o G , const it ut ing a ser ies w it h pit ch ra tio

a dva ncing from 0.50 t o 1.10, t he increa se in ra nge a long t he a xis of

~ 7/ n D ,with

a d wm cin g pit ch

w ill be not ed in t he va rious dia gra ms.

Likew ise, for a ny given va lue of V / n D , t he va lues of C T

a nd of C P t a re seen t o increa se cont inuously a nd a t a nea rly uniform ra te ba sed on increa se of

pit ch r a t io.

F or propellers w it hin t his ser ies (A t o G , inclusive), t he ma ximum or pea k efikiency is

gr ea t er for propeller s of h igh er pit ch r at ios.

For imy given va lue of V / a ll t here is but one propeller w hich is opera ting a t it s ma ximum

efficiency. H ow ever, it s efficiency is not t he highest w hich ca n be obt a ined a t t ha t ~ a lu e of


5/15

TESTS 03’ THIRTEEN NAVY TYPE MODEL PROPELLERS

155

17 nD.

here is one ot her propeller , ba ting a higher pit ch ra tio, w hich gives t he I @hest . possible

efficiency a t t he given

V/ nD for

propellers of t he pa rt icula r form used in t his series.

Th is is

cJ ea rly show n on Figure 28, w here cur-re N’o. 1 is dra wn t bough t he ma ximum or pea k eficiency

of ea ch propeller , w hile curve &70. 2 show t he ma ximum possible efhciency for ea ch T / n D.

Referring next t o t he result s for models K, M, C , L, const i~ ut ~ ~ a series on i ncr ea s in g b la d e

a rea , it -w ill b e not ed t ha t w it h t he form a nd proport ions of bla de sect ion empIoyed t here is but

slight ~ a ria t ion in t he ~ a ]ue of P /nD for ~ = ().

The ~ a lues of G , a nd C p, for a ny given -va lue of

V,lrdl increa se, how ever, cont inuously w it h increa se in a rea , a nd a ccorc@ t o a nea rly linea r

la -w over t he ra nge of a rea represent ed by t hese models.

For C , t here is, a s must be expect ed,

a n evident . t hough sma ll decrea se in t he ra t e of increa se of va Iue a nd, of course, w it h furt her

increa se in w idt h t hese va lues -w ould ra pidly a pproa ch a limit . The point of specia l int erest

in t hese result s lies in t he fa ct t ha i w it h t he genera lly ova I form of bla de cont our employed,

a nd w it h t he ma ximum w idfih va rying from a bout

0.07D t o O.10D ,

t he va lu es of t he coefficien ts

increa se nea rly in propor t ion t o t he a rea .

An exa mina tion of t he va lues for efficiency w ill show , how ever, t ha k in det a il a nd o~ er t he

w orking ra nge of 7T/nD t he ra te of increa se in fihe -due of t he pow er coefficient is grea ter t ha n

t ha t for t he t lw ust coefficient a nd t ha t in consequence, o-rer t his ra nge of F / n .D , in cr ea se in

a rea is a ccompa nied genera lly -w it h decrea se in efE ciency. This is ent irely in a ccord w it h

norma l expect a tion a nd likew ise w it h pret ious t est s rela fiing t o t he sa me point .

H .o~ e~ er , a s t here is some t endency t ow ard a n increa se of

V/ nD for T= Owith increased

a rea , it follow s t ha t t he efficiency for -re~ ; la rge -dues of F ln.D m ay be grea ter for la rge a rea

t ha n for sma ll. In consequence t he efficlerw y curves t end t o cross a t I a rge va lues of T’/nD ,

t hus reversing t he efficiency rela tion -w hich holds over t he w orking ra nge.

The a ct ua l -i-a ria tion of efficiency over t he w orking ra nge for t hese propellers is not ed t o

lie bet w een 3 a nd 5 per cent for a n a rea increa se of 50 per cenfi.

In compa ring t he result s for t hese four models it w ill be not ed t ha t t he a rea increment s a re

not eq ua I, t he successi~ e a rea s being in t he ra tio 0.80, 0.92, 1.00, 1.20.

As a furt her point of int erest , it w -ill be not ed t ha t for a rea cha nge t he va ria t ion in t he

va lues of (7T and C P I is rela tively sma ll a t la rge -m.Iues of V/nD a nd Ia .rge a t. s ma ll va lues.

Turning next t o t he result s for models C , H , I , J , const it ut ing a series on bla de t hickness,

it w -ill b e not ed t ha t t here is a ma rked cha nge in t he va lues of

??/ nD

for 1’= O, t he

value

increas-

ing w it h inc~ ea se of t hickness a s w ould be expect ed.

Likew ise, for a ~ given va lue of

T“htD,

t he -dues of (?T a nd C P I cont inuously increa se w it h increa se in t hickness, a t lea st over t he

ra nge represent ed in t hese modeIs. I t w ill a ko be not ed t ha t t he increa se in t he va lues of t he

coefficient s is rela ti~ ely la rge for Ia rge va lues of V/nD a nd t ha t it becomes ra arkedly less for

sma ll -ra lues, show ing a t endency t o disa ppea r a t ext reme va lues. I t w ill a lso be not ed t ha t

t his pa rt icula r t endency is t he reverse of t ha t not ed in connect ion w it -h increa se in a rea , -w -here

t he la rge ra te of cha nge is found for smfl va lues of

T T/ n Dand

t he sma ll r at e for la rge -dues.

Likew ise over t he w orking ra nge of T/nD a nd, a s w ould be expect ed, t he va lue of t he pow er

coefficient . incr ea ses w it h t hickness more ra pidly t ha n t ha t of t he t hrust coefficient a nd it r esult s

t ha t t he efficiency cont inuously decrea ses a s t he t hickness is increa sed. E ere, a ga in, t he

point of specia l int erest is t he rela t ively sma I l cha nge in efficiency lying w it hin 2 per cent ,

result ing from a cha ~~ e of 30 per cent in t he t hidcness.

L ikew ise, since w it h increa sed t hickness t he va lue of

V/ nD

for T= O i s increa sed, it follo-w s

t ha t for ~ ery la rge -dues of T ’/ n D t he efficiency w ill be grea ter for t he t hlek bla de t ha n for t he

t hin a nd t ha t in genera l t wo effic.ienc-j- cur -res for bla des of differing -dues of t he t hickness w ill

cross a nd t hus for ~ er-j- la rge va lues of F,’nll re~ erse t he rela tions w hich hold over t he w orking

range.

I n genera l t he result s found for t he t hirt een m odels w hich t he pr esent in-rest iga tions co~ er s,

a re ent irely h a ccord w it h result s found preciously

for models

of t he sa me genera I form a nd

pr oport ion. The r esult s of t he present in-i-est ima tion cont i, t herefor e, gener aI Iy simila r r esuhs

for like. m odels a nd furnish a dded series of perform ance coefficient s for propellers of t he form a nd

pr opor tion co-r er ed by t hem .


6/15

156‘

REPORT N.4TIONAL ADVISORY COMMITTEE FOR AERONAUTICS

TAB LE I

OBSERVED VALUES

PROPELLER A

A“

1,456

1,588

I, 712

1.899

2,093

2,334

2,560

2,845

3,022

3,264

1,756

2,375

——

1,319

1,426

1,556

1.719

1,905

2,114

2,338

2,547

2,769

2,972

3,334

1,831

C’r

I

CP1

—l—

Q

0.00 0.597

1.323 0.954

2.977 1.426

&204

2.032

8.272 ; 2. 76S

:;;; \ ~ :;;

21.17 6, 808

26.79 6.992

33.07.

8.386

ii: ] 2fi’3

0.0116

0.037 ~ 0.079

.0156

,Wl I

. 02cnl

.0232

g [ %

.0260

. Q79

.0278

.310 ;

1.546

.0297

.431 2.564

.0304

.558 3.889

.0315

.710 I 5.602.

.0324

.0329 . . ... .:. ~... . :-:??.

.0331 . .._...+ . .. . .

2,786

I

49.64

2.867

50.36

2.861

50.32

2.925 ; 50.86

2,899

3.088 ] a ;

p% , g:5J

3.240 ~ ::;::

3.249

O& 10.53

14.35

0.682

.634

. 5’%3

.536

.484

. 44S.

.410”

.379

.354

.3%

.119

.121

0.00

.0103

. 02C0

.028.9

.0371

.0430

. 0+86

.0528

.0576

.@309

.0839

.0841

.—

PROPELLER B

o.I-M

.0123

.0234

.03’41

.0435

.050$

.0566

.0623

.0669

.0718

.0761

.0969

0.

OJ

.051

.083

.130

.194

.279

.368

.488

.644

.812

1.109

3.169 I

3.088

3.141

3.162

3.‘X31

3.311

3.492

3.523

3.537

3.541

3.672 I

0.180

I

0.5’418

.9742

1.487

2.145

2.974

4.022

5.156

6.371

7,809

9.184

H.83

3.433

0.775’

: E

.606

.553

. m

.468

..432

. 3s9

.372

.338

.136

;

3

4

5

6

7

8

9

10

11

12

-.

PROPELLER C

—

‘“-r

—

- i i i l --- . .?:;: . _. ’_\_:.;.~

.......-

.0166 - -- :i ji ;- . ._Y&_:iG;.-

. . . . . . . -

.0302 ..-:iijG-- . . . . .iG.. ._.:ii:--

. . . . . . . . -

. . . . . . .- .0365

.119

.261

9

.0425 --.:iiG. ---------- .-. -:iG--

.0486

159 ,

. . . . . . . . :189

; :;: _.;:2:.- .__i+-:;..

.0606 .-.:6Z3-. ..----. -..;. ---:-----

. ot334 .317 1.158

.0674 . . ..i ii i.. . -..: iG:.. l...i :iGi ..

. . . . . . . -

; pl . . .. Gii.- . . . ..ii~.. ..-yijj. -

. 07s:

.0493 .677

3.878

.0811 . . .. 6;%. . --------------------

.0874

1.163 I 9.444

.0947

2.145 ‘. . . . . . . . . .

.1086

: :X . . . . . . . . ..] . . . . . . . ...\

1---~ ~---4376

.........

-----

l---i:326

. ..w.-

--------- - 1.467

2.980 . . . . . . . . . .

---------- : ;:;

. . . . . . . . . .

5 .294 ----------

8.272 3.165

. . . . . . . . . . 3.094

8.272 . .i .i ii -. .

: 11.91

11.91 --


7/15

TESTS ON THITWE.EN NAVY TYPE M.ODEII PEOPEZLEES

TAB LE I -C on tin ued

OBSERVED VALUES—COntinQed

PEIOPELLEE F

CT

0.0’3

.0266

,0481

.O@-53

; g%:

. (Ni8

.1044

.1090

.1146

.1326

0.(M

.0307

. O@-

.0729

.0876

.Owl

.1069

.1142

.1203

.1234

.1331

.1403

T

CFJ

h-o.

~pm ~ T

—

3.146

5266

3.1’33

53.06

3.168

52.87

3.177

52.94

3.267

53.68

3.330

54-22

3.3-% :

.54.69

3, h~ ,

55.22

3.483 ~ 55.49

3:~J [ yg

,

0:&i \

L 201

1:;3

1.W4 ;

2.662 ; ;=

3.765 ;

5.126

.672

6.584 I

.607

8. 234 ~ .553

10.C03 ~

.505

11.910 ~

.469

3. 32T

. m

1

2

3

4

5

6

7

8

1:

11

—

PRoPEILER G

-

1

2,

3

4

~

6

7

s

@

i

0:Ml&

0. Cdxi

t

.023

. %35

. ~~

- 1~~

.142

.1810

; $g

.2643

. 3i70

.944

.5245

1-620

2.623

:7E 3.915

--- -- -- --- - -_. —-_

--- -- - - -- -

----.--—.

1.31XI

L 153

1.016

.W1

. y

. [05

.632

.569

.517

.478

.167

.177

PBOPEmR H

3.141 ‘

3.199

3.25s

3.145

3.352

3.433

3.2i6

3.321 ;

3.402

3..505

3.631 :

.124 ,

~ 13’4

:&l

1,321

1,736

L 941

1,W3

2, IC6

2,323

2,533

2,75.5

I, 433

0.02

.0163

.0299

.0439

.0535

;(M&

.0733

.0756

.Oso-5

.0340

. m4

0.01S I

.041 i

.070 ,

::j I

-261

.263

.3ii

.501

$33

-1

-------- ---

0.022

.058

.119

.2-5s

.458

.818

.855

L 456

2.297

3.345

4.721

,-- .-—-.

;

3

4

5

6

7

8

1;

11

12

52-09 ;

52.5+5

.53.35

1

52. s2 {

54.21 I

.5L36 c

53.18

53.62

$4.32

55.14 ;

56.12 ,

10.35 ~

—.

I

I

PRoPEIJ.EE I

0.025

.046

.069

.092

.107

.144

.179

. 2Kl

-326

.440

1: g

.--.—-

——

PBOPELLER J

PROPELLE13K

52.10

1,193

0.03

&414

0.875

0.co

~2.2,j

.53.w

?:2 ~ %

;=

%J

%g

52.89

1:652

53.26

L873 ~ ~~~

295-4

.569

.0466

54.26

3.954

.516

;@&

.54.33

;% j ;6..;

5.095

.4e6

-

54.83

&5i2

6.352

.477

.0634

5.5.26

; S&

26.79

7.ml

.393

. Q671

15.35

,

26.47

5.446

.133 .0920

~~

3. w

:

3.073

i3

3.159

~4

3. Ill

f~

3.186

16

3.2?5

17

3.307

3.375

: t 3.422

~lo~ o. 2s3

o.

(LX

0.018 I 0.023

.0195

.6$0 , .C6-5

I

. 0%9

-~~ ,

.143 I

.cm4

.12u , .x?

. e349

.189 .58.5

.0371

270 \ L 014

.0389

:3?4 ] Lzo

.0399

.513 I 2.812

-0403

.W

.m

_.._+5? _

1


8/15

REPORT NATIONAL 44DVISORY COMMITTEE FOR AERON.4UT1CS

TAB LE I —C on tin ued

OBSERVED VALUl?S-Continued

PROPELLER L

1

I

.- . . .7.

iv

T“

CP1 CP2 C’P3

0.028

. (M8

I

.126

.241

.453

i R

2105

3.053

4.515

. . . . . . . . .

v

Q I V,nD

0,524 0.893

L 028 .2.27

1.585

.767-.

.2 .378

7Q

3.326 :634

4,4-

.577

5.7. . q

7.260 .3

8.862

,451

10.Oai .419

2524 .148

0.00

1.323

2.977

5.292

8 . 2 8

11.91

16.21

21.17

26.79

33.07

11.02

1,151

1,257

1,385

1,540

1,702

1,892

2,104

2,307

2, m

%719

1,285

0.022

.046

.074

.118

.182

.265

.363

.492

. w

.793

......-.

PROPELLER N

—

0.875

. SW

.742

.671

.603

.537

.487

.454

.422

.393

.137

0.019 : 0.025

.041 .Iw3

.068 {

.124

.111 / .247

.173

.476

.274 ‘

.952 I

. 3S3 ~ 1.614 \

.472 i -

.615 , : M ~

.779 5. c-is ,

------- .+.. -. . . .-

1

0.of

L 323

2.977

5.292

8.268

11.91

16.21

21.17

26.79

33.07

11.02

_

—

I I

ADJUSTED VALUES

Q

Prop.

F

lB”’c D\~

:—

7P

w,

CP1

7

CP1

— —

I

--------------..:-. -----

.-................

I_

v

CP1

—

. . . . . . . . . . . . . . . .

0.549 . ._ -.-.. .

.601 . . . . . . . . .

.644

0.0623

.$:: ml;

. ~39 .0577

: % :

: l%:-

.0485

:p~~

.618

:%

:::+ :029:

. . . . . . . . . .

—

7

cm

v

—— —

C’P1

------- .... ----.

-------

.--- _=-.... ...-

-------

...---- ...------

--------

.... .. ..-------

-------

0,604

0:m:

0.586

. fi46

.628

.0718

T

-

.667

.715

.0705 , .701

.745

. Ow

.732

.766

. @63

.75$

.779

.6332

.7.82

.7112 .0597

768 ; O& \

::::

:731

. awl

. 64L .0460 .783

.445 .0401

--- —. .0331

:2

. ..——

.0245, .471

-------------- .

-------------- -.

----------- -----

-------- .... .....

0.0326

0.594

.0316

.637 I

. Q3m

.669 /

.0280

.689

.Wo:

.690:

. 02XJ

.660

,0184

.571

.0143. .323,

.......;.

0.566

.622:

.655

.699

.730:

: M

.663,

.557 ,

I

;

.65

.70

.75

I

.80

.85

.90

I

.95

1

1.m

1.05

1.10

-------------

.-.1

—.

.0233

------

~

...... .-------

.--..--:.....- ..

.... ... --------

------- ....... .

.--------- ----

-------

-.-— ---------

--------

.J........

.......

-______.......-

------.-._... -------

-------- -------

ADJUSTED VALUES

Prop. ~

H

I

J

vlnD- ~

fP1

1

CP1 ~ v

G

I

~

——

.

L-l-4

0.40

.45

.53

.55

.&l

.65

.70

:1

0.0530

.0519 ~

.0503

.0480

.04$2

.0418

.0379

.0335

.0287 ,

0.639

.676

:%?

.152

. j60

.:56

: iti

0.0553

.0545

I

.0532 f

.0515

.0494 I

.0482 [

.0426 f

.0388

.0347

0.532

.670

.7@

..7-30

. 7B

.J53

.756

.730

. 66S

0.0563

.0558

.0546 c

; g:; 1

.0492

.0468

.0441

.0408 j

0.628

;::

.124

I44

:753

: ; ;:

.687

.4DJI_isTED V.4LUES

I

Prop, ,

K L

M

v/711) ~

C’P1 I 7 CP1

0.40

.45

.50

.55

.60

.65

:;

.80

0:::::

; ::: ~

.0330

.0299

.0262

.0224

.0184 ,

0.657

.691

722

: 761

.767

: M

.6$9

.544

0.607

.651

.690

. ~19

.144

7.51

:742

. 6~9

.619

0.649

.685

. y7

.:45

.:62

. ~6~

: &

.575

I


9/15

TESTS ‘ON THIRTEEN NAVY TYPE MODEL PROPELLERS

159

—

FIG. l.—Pro@fer A. Diameter, 3 feet. Aspect ratio, 6. M*UJZI

blade width, 3 inches. Pitch, 18 inch-. Pitch ratio, 0.5. Camber

ratio, minimum

1

Fw

L2.@L

+3.5”D4

&202”+

1+.94”A

I

—3.504

l+94”A

EIG. 2.—Pro@fer B.&Diameter , 3 feet. .Lspect ratio, 6 . Maximmn

blade width , 3 inches. Pitch , 21.6 inches. Pitch ratio 0 .6 . Camber

ratio, rninfmwn

I-2A-4

L3.J”D-l

L?;s_

FIG. 3.—PmpelIer C. Diameter, 3 fee t. L .p-ect ratio, 6. Mesimuxn

FIG. 4—Propeller D. Diameter, 3 feet. i@ect ratio, 6. Maximnm

blade width, 3 inches. Pi tch, 25.2 inches. Pitch rat io 0 .7. Camber

blade width, 3 inches. Pitch , 2%Sinches. Pitch rat io 0.8. Camber

ratio, minimum

ratio, min imu m


10/15

REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

FIG. .5.—Propdler E. Diameter, 3 feet. .kspect ratio, 6. Maximum

bk.de width, 3 inches . Pitch, 32.4inches , Pitch rtitio, 0 ,9 . Camber

raclo, minimum

FIG. 7.—Propeller Cl. Diameter, 3 feet. Aspect ratio, 6, Maximum

blade width, 3 inches, Pitch, 39.6 inches. Pi tch ratio, 1,1. Camber

ratio, minimum

..

-’–IL---LY

m. 6.—Pro@ler F. Diameter, 3 feet. .4s~ct ratio, 6. Maximum

blade width, 3 inches. Pitch, 36 inches. Pitch ratio, 1. Camber

ratio, minimum

FIG. S.—Propeller H. Diameter, 3 feet. .kspect ratio, & Maximum

blade width, 3 inches. Pitch, 25.2inches . Pitch ratio , 0 .7 . Camber

ratio, minimum +10 per cent


11/15

TESTS ON TH~TEEl” NATY TYPE IvIODEL PROPELI RS

161

—.—

h

>

—.—

L-1

m.

.—. —

>

0

+“—-—

.

g. —..

~.__

.

..—

4

FIG. 9.—Pro@ler I. Diameter, 3 feet. Aspect r@io, 6. Maxtmrm

blade width, 3 iuches. Pi tch, 25.2 inches. Wch rat io, 0 .7. Camber


FIG. Io.—propclk J. Diameter, 3 feet. Aspect ratio, 6. Ma.rimum

blade width, 3 inches. Fi tch, 25.2 inches. Pitch rat io, 0.7. Camlmr


.y_Q_L-

1—

1“

-.4LJ-Q

—

I%. 11 —pmpelk K Diameter , 3 feet. Aspect ratio, 7 .5 . Mazimmn

FIG. 12.—PropelIer L. Diameter, 3 fee t. Aafwt rat io, 5. Maximum

blade width, 2.4 inches. Pitch, X,2 inches. Pitchratio, 0 .7 . Camber

blade width. 3.6 inches. Pitch, 25.2inches . Pitch mtio, 0 .7 . Camber

ratio, minimum

ratio, mfuimum


12/15

162

REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

0—4

Lid

B/odefhicknessrordhote

5.0

u

10 20 30 0 50. 60 70 80 s?0 100Z

k

Bk7dewidfhor chord

–J

FIG. 14.—Strmdrtrdblade section

.20 ./0

I

./6 .08

.8

./2 .06

.6

CT G,

—

— v

.08 .04

c,

.04‘.02

V/nD

FIG. 13.—Propelle r M. Diameter , 3 fee t. Aspect rat io, 6.5 inches.

FIG. 15,—Propeller A

maximum blade width, 2.77 inches. Pitch, 25.2 inches. Pitch ratio,

O.7. Camber ratio , minimum


13/15

TESTS ON THIRTEEA-

.20 .io

-1

.16 .08 :’

1

,?

.8

,

./2 .06

.6

v

.4

.16 .08 ~’[

[

.08 .04

.04 .02

I

I

o L70

I

,2 .4 .6

.8

-a

V[72D

FIG. ii.—Propeller C

.20

./0

I

I

~.

1

;dm~~

“AVY ‘TYPE MODEL PROPELLEES

163

.20 .10- I

./6 .08

J , .~ ‘2 ~.

.8

\

.12 .06

— — ‘

/ ‘~ *

\l

.6

7

\

CT c?,

?7’

.08 .04

~

\

II

.4

/ d

& \

\

\

.04 .02

1

.2

I

o 00

2 .4 .6’

I@@

g

FIG. 19.—Pro@le r E

.

.20 .[0 f

./6 .08-

.8

./2 .06

-t-k ./ ‘

IN t ‘,

/Y.

\ ‘\ “6

c= CPI

/ ‘

T

.08 .04

C,y

/

\

\

.4

/

.04 .02

/

f

IIIN

.

0 00

.2

.4 .6

.8

Lo

v/nD

FIG.ZO—Pro@lw F

ic

.

/2 .06 :

Cr CF1

I

I

1

i:

t

04 .02 ;;

\pJ

I

il ilk

ill

~. ~

o 00

.;

.4

.6

.8

t ~n D

FIG. lS.—Pro@ler D 7

I \ j

I

./2 .06

CT &

.08 .04

.04 .02 .2

0 00

.2 .4 .6

.8

‘ 0

‘ 2

o

v/72.o

FIG. 21—Prop?ll e: G

II

,’ , ;f


14/15

164

EFFECT OF ELIGHT I?ATLI INCLINATION ON AIRPLANE VELOCITY

.20 .10

./6 .08

.[2 .06

G c,,

.08 .04

/

.04 .02

1

V n D

FIG. 22.—Propeller H

.20 ,/0

Ii

f

ill

/6

.08 ,

,

T

.8

—

i’

.12 .06 :

/

I

.6

CT c=,

i

\

\

v

I

.08 .04 ~’,

\

.4

1,

\

I

I

.04 .02

I [1 ‘~ \

\

,2

0 00

.2

.4 .6

.8

v/7zD

FIG 24.—PropAler J

.20 ,/0

I

I

/

./6 .08

II, ,

.8

*

,

1

.[2 .06 i“L

,

G

I

.6

0 >/

c? Cpl

I

\

v

1 i/

,’ 7

08 .04 ;

.4

/,i.

c: \

~’~ ~ [

L

.04 .02

2

flt~

/lt(

o 00 i .J i .4

.6

.8

/.0

o

V f nD

FIG. 2 -PrOpeller L

.20 .10

f

.16 .08

v ,—

.

.,

\

. 2 .06

/ ‘

> q A y

ji& ~

\

,

c’~ Cpl

“Q

.08 .04—

.04 .02

V n B

FfG.

23.-Propeller I

.20 ./0

.16 .08

v +

1

.8

/

.12 .06

/ d

\

-.6

c= C?f

/ ‘

Q

.08 .04

/

— .4

/

5

\

.U4 .02 h

* .2

\

\

o 00

.2

.4 .6

.8

10

0

v/nD

FIG. 25—Prop+ller K

.2Q ..fo

I

.16 .08

.8

1

7/ / ~

./2 .08

/ y

c, c?,—

.08 .04

}

> \

,04.02

*

\

,2

\

o 00

.2

.4 .6

.8

10

0

V n D

FIG. 27.—Propeller M


15/15

TESTS ON THIRTEEN NATW TYPE MODEL PEiOPELLEFW

165

TJ

nil

FIG.n.—Pm@ler efficienciesfor various PIDratios and WnD. Based on *~ ~~r ad SSWet ratiO 6

Documents

NASA Tests on 13 Navy Type Model Propellers