NASA Tests on 13 Navy Type Model Propellers
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Transcript of NASA Tests on 13 Navy Type Model Propellers
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REPORT No.237
TESTS ON THIRTEEN NAVY TYPE IMODEL
PROPELLERS
By W. F. I URAND
Stanford University
-Q4SS—27—11
151
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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
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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 .
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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 --
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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$0 , .C6-5
I
. 0%9
-~~ ,
.143 I
.cm4
.12u , .x?
. e349
.189 .58.5
.0371
270 \ L 014
.0389
:3?4 ] Lzo
.0399
.513 I 2.812
-0403
.W
.m
_.._+5? _
1
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8/17/2019 NASA Tests on 13 Navy Type Model Propellers
8/15
REPORT NATIONAL 44DVISORY COMMITTEE FOR AERON.4UT1CS
TAB LE I —C on tin ued
OBSERVED VALUl?S-Continued
PROPELLER L
1
I
.- . . .7.
iv
T“
CP1 CP2 C’P3
0.028
. (M8
I
.126
.241
.453
i R
2105
3.053
4.515
. . . . . . . . .
v
Q I V,nD
0,524 0.893
L 028 .2.27
1.585
.767-.
.2 .378
7Q
3.326 :634
4,4-
.577
5.7. . q
7.260 .3
8.862
,451
10.Oai .419
2524 .148
0.00
1.323
2.977
5.292
8 . 2 8
11.91
16.21
21.17
26.79
33.07
11.02
1,151
1,257
1,385
1,540
1,702
1,892
2,104
2,307
2, m
%719
1,285
0.022
.046
.074
.118
.182
.265
.363
.492
. w
.793
......-.
PROPELLER N
—
0.875
. SW
.742
.671
.603
.537
.487
.454
.422
.393
.137
0.019 : 0.025
.041 .Iw3
.068 {
.124
.111 / .247
.173
.476
.274 ‘
.952 I
. 3S3 ~ 1.614 \
.472 i -
.615 , : M ~
.779 5. c-is ,
------- .+.. -. . . .-
1
0.of
L 323
2.977
5.292
8.268
11.91
16.21
21.17
26.79
33.07
11.02
_
—
I I
ADJUSTED VALUES
Q
Prop.
F
lB”’c D\~
:—
7P
w,
CP1
7
CP1
— —
I
--------------..:-. -----
.-................
I_
v
CP1
—
. . . . . . . . . . . . . . . .
0.549 . ._ -.-.. .
.601 . . . . . . . . .
.644
0.0623
.$:: 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
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8/17/2019 NASA Tests on 13 Navy Type Model Propellers
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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
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8/17/2019 NASA Tests on 13 Navy Type Model Propellers
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
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8/17/2019 NASA Tests on 13 Navy Type Model Propellers
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
ratio, minimum +20 per cent
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
ratio, minimum +30 per cent
.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
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8/17/2019 NASA Tests on 13 Navy Type Model Propellers
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
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8/17/2019 NASA Tests on 13 Navy Type Model Propellers
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
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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
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8/17/2019 NASA Tests on 13 Navy Type Model Propellers
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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