REPORT NO. 436

TESTS OF NACELLE-PROPELLER COMBINATIONS IN VARIOUS POSITIONS WITH

REFERENCE TO

INGS-TRACTOR

WINGS. IL—THICK WING-VARIOUS RADIAL-ENGINE COWLPROPELLER

By DONALD H. ‘WOOD

SUMMARY

This report is the second of a 8eTiee@ing the results

obfain.edin the .%?O-foot wind tunnel of the National Adoi80~ (?o?nrnitteefor Aeroruudia on the inienferen.wdrag

and propulsive ejbiency of nucelle-propelleraing cOmbinutti. The jir8t report gave the r& of the teds

of an A? A. C. A. cow.kdair-cooled engine nuceUelocated

in 2?1 positions with reference to a thick wing. The

pre8ent report gime reswlis of te3t8of a nmnud engine

nacelle with sevend typtx of cowling andfairing8 in fowr

of the posi.thna m“threferm to the same wing.

l%s wing had a 6~oot chord, a 16#oot span, and a

maximum thi.cknes8of 20 per ceni of the chord. The

engine was a 4/9-sc& model of a Wr-i@ J–6 radia+?aircooled engiw, and waa imtalled in a d nacelle of

the8ame8cd.e. Testi were mudewiih no cngin.ecowling,

with a narrow variabkwzngb ring, two wida thin ring8

with di$ereni chord angles, and the hood previously used

on tlw N. A. C. A. cowlednucelle. 17wpropei?l~w a

4#oot diumeter model of the 8tandardNaoy adjwtabbpitch metalpropeiler No. al~.

In two of the nucelle podti tats were & in two

condiiio~h tlw nacelle supported on stnd8 and

with the space betweenthe nacelle and wingj?.ted byfairing. The e~ects offai.ring the N. A. C. A. hoodinto -the

wing and of side brackets on the nad.le when located

ahead of the wing were do instigated.

Tlu .hjl, drag, and propw%ioe q%iency were deteTrnined at 8euera.1angles of dtack for each cowling and

fairing condition in each of the four nacelle locati.ona.

Z%enet @%iency wm conqmdedby the method cj Report

No. 46 and comparedwith the rewlis thereinreported.

Although thepropul-w%e@%ienqI of tlu d uncowled

nuc~ ix higher than that of tti nacd?.edh @?ly of the

cowling8, the drag and intq%remx are do higher, and

tti highed net ejiAenq h obtainedwith the N. A. C. A.

cowled nucella. Fairing the nacelk into the wing G am

aduantagewhen t?w cowled nuceila are located ntxzr the

wing buti-sof littlevulwewhenthenacelles are not cowled.

.Fah-iWtlwN. A. (?. A. hoodinio the wing h detrimental.

Side bracket8on tha nacelle when ii h hated ahead of

thewingare to be avoided. Ttw N. A. C. A. cowled

nacelle lacatedabout M per cent of the chordahead of the

wing G tlu besttractor-nacel.barrangement. If the cowling h omitted with nacelle in this posiiion, a 1088of lift

T&, especidy at high angles of attack. The proper

l.ocaiionof nadle.s and cureful cowling are importani in

the high-qwd ramgeof$igh$ M in the lower speedrangtx

there i8 liztleadmntage of one na42Ueposition or cowling

008Tandlwr.

INTRODUCTION

This report is the mcond of a seri~ giving the results

of ageneral investigation of the mutual effects of wings,

nacelle-s,and propellem. Originally presented at the

Fourth Annual Aircraft Engineering Research Conference in May, 1929, the program has been subsequently extended and now includes tractor, pusher, and

tandem propellers, and biplane as well ss monoplane

wings. Several propeller pitch settings and numerous

types of engine coding have also been included.

The fit report (reference 1) gave the results obtained with an N. A. C. A. cowled air-cooled e~”ne

nacelle located in 21 positions with reference to a thick

monoplane wing. The results indicated that a position of the nacelle directly ahead of the wing was the

best. If practkd considerations demsnd 1ss.sfavorable locatiom, the nacelles should not be placed too

close to the wing above or below. The use of cowlings

on radial air-cooled engines haa been uniformly successful. Many installations, however, have been, and

probably will continue to be made without oovd.ing

over the engine, or at least with simpler forms of ccnvling. That cowling is an advantage is a stioient reason for msking the extensive series of tests of reference 1; but it is also important to know something of

the effects when the engine is not cowled or is fitted

with other forms of coding.

This second. report in the series therefore presents

the results obtained with an engine nacelle of the type

commonly used with uncmvled engines. This naedle

was tested both uncowled and with four cowlings which

experience and a study of exkting airplane designs

indicated were most eiiicient or were in common use.

653
—— —.. ---- —..-.—- “.- ------ ----

654 REPORT NATIONAII ADVISORY COMMITTDE FOR AERONAUTICS

Four nacelle positions were selected from the original

series-the position ahead of the wing -which the fit

tests had shown to be the best and three others, one

above and forward of the wing and two below the

aud because of other design restrictions. Other locations aivay from the wing may be slightly better, but

it is hardly worth -whileusing them except in special

csses. In each nacelle position the four types of cowlR_ AFIGURE L-SmEII .mcdle anden#ne @s9111tdy

—DA +6

7hfwst Jine

—20.

4A *B

Secfibn kA .%chbn B-B Section C-C Seci%m D-D

IymEllz*.A. c.A.un71ednacen eand6ngin0a%s31nkdy

wing. The latter three positions were selected mainly ing were tested both with and without propeller

because they have been commonly used on airplanes operating.

constructed in the psst and alsobecause they are likely Whethar or not fairings shall be used is always a

to continue in fairly general use for structural ressons moot question in airplane design, and accordingly the
NAOEILlilI COhl131WATI.ONS ~ VARIOUS POSITIONS WITH REFEFU3NCEI TO WINGS- 655

effect9 of fairing the nacelle into the wing were investigated. In the course of the investigation certain other

perhaps incidental items appeared. When the nacelle

vm.eoriginally installed ahead of the wing, it was supported by angle brackets which protruded from the

sides of the nacelle and were covered over with fairings. These brackets were later removed and repeat

tcd.s were made to determine the effect of such appendages. When the nacelle is very near the wing

and far back the cowling hood intersects the wing.

The question of whether the resulting hollow should

be faired arose, and the results of the tests are given.

Whenever possible, comparisons of the rwdts with

those of the first series have been made.

The test program having assumed large proportions

it was necessary to limit the number of teats, and in

consequence the results axe perhaps open to criticism.

Although the teat rceilts do not represent the ultimate

that can be obtained with simple cowlings, they do show

the interference effects to a good approximation and,

taken with the results for the N. A. C. A. cowled

nacelle, pre9ent a fair picture of the relative merits

LRU

~GUEE 3.—Variableagle ring

of tractor-propeller radial-engine nacelle and wing

combinations.

APPARATUS AND METHODS

The propeller-research tunnel, in which the &ts

were made, is described in reference 2. The standard

apparatus and test methods were used with certain

exceptions mentioned later.

The wing is constructed of wood with a s-foot

chord and a 15-foot span. The airfoil section, the

ordinates of which are given in Figure 1, reference 1,

has a maximum thiclmess of 20 per cent of the chord.

The central portion of the wing is provided with

suitable metil ribs and plates for the connection of

the struts required in attaching the nacelle to the wing.

The engine nacelle constructed of sheet duralumin

was similar to nacelles required for a Wright J–5

radial engine, and was four-ninths (0.445) W scale.

A detailed wooden model of this engine was installed

in the proper position in the nacelle. This nacelle was

comtructed with the dimensions given in F&me 1,

and represents a normal nacelle such as is employed

when the engine is uncmvled. All the tests of this

report were made with this nacelle (called smallnacelle)

and model engine. A larger nacelle fitted with a hood,

the nacelle and hood constituting an N. A. C. A.

cowled nacelle, was used in the tests of raference 1

and the hood was used in some of the tests of this

report. The principal dimensions of this na@le and

the hood are given in Figure 2, which is reproduced

from reference 1 for comparison.

—9y

3

.+ o“

$

—.

.—— .

I

~GUEE 4.-Ring No.1

The four cowlings fitted to the er@ne and end

nacelle were of thr~e distinct types: A-naxrow multisided ring, the angles of the sides of which could be

adjusted; two wide thin rings with their chord lines 0°

and – 6.3° to theaxis; and thehood previously usedwith

the N. A. C. A. cowled nacelle. These are designated

variable-sngle ring, ring 1, ring 3, and N. A. C. A.

hood, respectively, for purposes of reference. The “

principal dimensions are given in Figures 2,3,4, and 5.

h preliminary tests on the nacelle alone, tobe discussed

in a later report, another ring (ring 2) having an angle

Fl13mm5.—Rfng No. 3

of —3° was tested but showed no promise; consequently

no further teats of it were made.

The wing-nacelle-propdler combination with the

various cowlings was tested with the nacelle and wing

in the four relative positions marked in Figure 6. b

the iigure the crosses indicate the positions of the

center line of the propeller hub. The nacelle positions

are designated by the system of letters shown.

The design of the variable-angle ring was based on

the tests of reference 6 and the angle setting was

determined in the preliminsxy tests. The – 8° setting

was found to give the lowest nacelle drag and was

therefore used in the present tests with the wing.

.
————. ~. - -------~ d656 REPORT NATIONi3J ADVISORY CO hlMfTTEE FOR AERONAUTICS

The variable-angle r@ and also the N. A. C. A. hood

were located on the nacelle with their leading edgea

=-A12‘

j> A-I-A B-fA C-f”

5 ft. chord

fhic+c wing a

. .

q~+ L2&&

a

a.14y6” A -/B B-!-B C-!-B

1

7 T T

L?’

‘=?77

A-2-B B-2-B C B

x MA.(2I. cowl My

8 Vmbus cowlings 12”

A-3fl BG’-B C-3+ -

---

FIGURE 6.-THnE-nadle & kcxfom

5X inches ahead of the center line of the engine

cylinders.

Rings 1 and 3 were each located in two fore-red-aft

positions-position 2, 4ji inches, and position 3, 3%

inches from leading edge of ring to center line of

cylinders with the nacelle in position B. Ring 1 rLppeared poor in both positions and ring 3 was better in

position 2. The tests in othe~ nacelle locations were

therefore made with ring 3 in position 2 only.

The propeller, which is 4 feet in diameter, is geometrically similar to the NrLvystandard 4412, 9-footdiameter aluminum alloy propeller. A number of

full-scale tests of this propeller have been made and

are described in references 2 and 3. The blades may

be turned in the hub to give different pitch settings.

In the tests discussed here, the pitch setting ma 17°

at 0.75 R, which is about average for usual operating

conditions. This is the same pitch used in the tests

of reference 1 and results are therefore directly comparable.

For driving this propeller, a 25-horsepower 220-volt

direot-ourrent motor ma mounted within the nacelle.

Wires were led from the motor down the struts into the

w_&, ~d aloqg the supporting members to the control

equipment on the floor below. These wires were carefully taped to the struts, preserving a streamline shape

which, in subsequent tests, showed a negligible effect

Fmmm 7.—Photugmphof wfwmdle comblnntfonfn @tlon B-l-A mormtd forte?t
NACELL13 COhD3~ATIONS IN VARIOUS POSITIONS WITH IZEFERENCE TO WINGS 657

on the tare drag. A Prony brake was used for calibrating the motor, and curves were obtained giving armature current against torque for several values of the

field current. During the tests the field current was

held at one of these calibrated values. Revolution

speed was indicated by a condenser-type electric tachometer which occupied a small space in the nacelle and

was connected by wires to an indicating instrument on

the floor below.

The wing and nacelle combinations were mounted on

the balance by means of standwxl supports, which have

been described in reference 4. Vi5ththese supports the

airfoil pivots about a line near the lower surface 25

‘per cent of the chord back from the leading edge, and

the angle of attack is adjusted by a crank operating a

post connected with a sting on the airfoil. The airfoil

and nacelle mounted in one test position are shown in

Figure 7. Figures 8, 9, 10, and 11 are photographs of

the other wing-nacelle set-ups, arranged in the order

of the nacdle locations and cowlings. In all cases, the

thrust line of the propeller vw fixed parallel to the

wing chord.

I’or use in subsequent analyses, n series of tests at

various air speeds was made with the mungalone at

angles of attack of – 5°,.00, 5°, 10°, and 12°. Similar

tests were made with the small nacelle alone. In each

case separate tare-drag teats were also made. The

lift and drag forces were measured simultaneously by

balancea on the floor below. The Reynolds Number

varied from about 2,300,000 at the lowest air speed

(54 m. p. h.) to 4,300,000 at the highest speed

(99 m. p. h.).

The first test with each combination was a run at

several air speeds, with the propeller removed. The

lift, drag, and air speed were measured. A second teat

was then made with the propeller in place, and with

the tunnel operating at several air speeds. In this

tit the lift, drag (or thrust), torque, propeller revolutions, and air speed were measured. Separate tests

were made at angles of attack of —5°, 0°, 5°, 10°, and

12°. At the 12° angle only a few points were deter

mined near zero thrust. I

With the nacelles in positions B-l–A and A-l–B the

tests were made both with the nacelle supported by

struts only and with the struts surrounded by a

faking joining the wing and nacelle. With the nacelle

in position B the supports as originally installed protruded from the sides of the nacelle. These brackets

although faired were considered to be of doubtful

utility and accorchgly repeat teats were made with

them removed. The fairings and struts are clearly

shown in the photographs.

With the nacelle in positions A-l–A and A–l–B the

engine coding intersects the wing in a manner that

may account for some unfavorable interference. In

the tests of reference 1 the cowling was faired into the

wing as shown in the photographs at the right of

Figure 12. Airfoil tests were later made with the

hood fairiug removed as indicated at the left of Figure

12, and the comparative results are given here.

RESULTS

The meamired lift and drag were reduced to the

usual coefficients

~L_ Lift ~ = Moment QD=D~ ~

qs qsc

where

g, the dynamic pressure (% PV).

p, maw densi~ of the air.

V, velocity.

S, the area of the wing.

c, the chord of the wing.

(All moments are taken about the quarterchord point of the wing.)

These coefficients were fit plotted against the

dynamic pressure q and then cross plotted as CL,

CD, and G. against a (angle of attack) at values of

the dynamic pressure corresponding to 50, 75, and

100 m. p. h.

Since the principal interest is in the comparative

results with various cowlings in the diiferent positions,

the lift and drag coefficients have been plotted as polar

diagrams arranged in a manner to facilitate such comparisons. The N. A. C. A. cowled nacelle is nothing

more than an improved engine cowling and should

obviously be examined with the other types. Accordingly, in the photographs, figures, and tables information from reference 1 has been included to complete

the series.

Inl?igures 13to 16polar diagramsaregiven of the lift

and drag coefficients obtained with the various coTvlings in the four nacelle positions. Figures 17 and 18

show the results for positions A–l–B and B-l-A with

and without fairi.ng. Figure 19 shows the effect of

side brackets on the nacelle in position B and Figure

20 the effect of hood fairing on the N. A. C. A. cowled

nacelle in positions A–l–A and A–l-B. Figq.re 21

compares the results with rings 1 and 3 with those

for the variable-angle ring. Figures 22 and 23 show

the comparative results for two cowlings in all four

nacelle positions, Figure 22 the small nacelle without

cowling, and Figure 23 the N. A. C. A. cowled nacelle.

All these diagrams are plotted from the data obtained

at an air speed of 100 m. p. h. The results are also

given in Tables I and II, together with those for two

othei air speeds, 50 and 75 m. p. h.

The results with the propeller operating are reduced

to the usual coefficients

T– AD CT.— P

oP=~p p n=P
8meJlnncoll~oxpcmdoyllndor&W Intowing, Smnllmmllo,ringNo.3,fdmd intowing,

\

mCn

w s

i

[

BIIMIJWOU%*ble@q40 I@ set -W, fokedinto wing. Smallnacelle,N. A. O. A. hid, falrodIntowing. N. A. O. A. cowkl nomlle[not frdmdintowing.

fi9UEE S.-NacaUm h ~itfOtl B-l-A

.
Smrdlnamllo,ox@ oyllndomwltb aidebrooketfalrfng, Smrdlnaoelk OXIMA whdem Withoutsidebraoko~. Smd noeallo, ring No. 3, withsidebmoket fofrlng.

Smnllnam)lojvorlnblo+mgloringent-8”. Small mmllq N. A. O. A. head. N. A. 0. A. CX3\VhdtMI@3u0.

~aun~ 9,–Nncoflm inpmltfonB
Srnollnnmllo,oxpcmdoyllndom,not fotrodInto wing. Smell nnmllo OIpceodoyllndota,frdrodintowing, SmnllnnmUo,ringNo, 3, fnlmdIntowing.

Small mmlle, vorloblwngleringset -W, folmdIntowing. SmollnmeIlo,N.A, O. A,h@faimd Intowhg. N, A. O. A. CYJwlednacell~folrodIntowing,

?i’faum l&—NomlIwinxmdtlonA-l-B
Srndlnmllo, oxpumdoyllndem

bd M~O, variablwglo I’iIlg@lt.-&, fhnall@o, N, A. 0, A. hood, N. A. O. A.:cowM nacelle.

FIaum lL-NncollIw InpodtlonA-2-B
------ --- --- . —-,—---- ..-=... + —.. . ~ —-. . .

662 REPORT NATIONAIJ ADVISORY CO~ FOR AERONAUTICS

where

T, thrust of prcpeller operating in front of a

body (tension in cranlmhaft).

AD, change- ~ drag of body due & action of

prcpeller.

T– AD, effective thrc.st (discussed in reference 3).

n, revolutions per unit time.

D, propeller .diametar.

P, motor power.

1

VIII, Moment CoefEcient with Propeller Operating

(U~P). The plots of these results follow the normal

trends of prcpeller characteristic curves and, since only

individual values are used in later comparisons, no

cm&s are reproduced here. The reader is refwed to

reference 1 for a-typical set of such curves. ‘

ACCURACY

All readings were taken OQscales and instruments

that were calibrated frequently during the tests. The

N. A. O. & WWIMnmd.lein POWJJnA-l-A, tithent hcod hlriu.. N. A. O. A. cowlednacdle in pmitionA-1-A, withhcmdWing.

N. A. O. k corded nacalbin PC&tienA-1-B withcmtW f81rhI& N. A. O. A. COWIM3na@e in pmitionA-l-B, withhmd fdrlng.

~GUEE 12-N. A. O. A. cmvkxlrceceIlewfthand withouthood(eking

and

q= propulsive efficiency

= effective thrust X velocity of advance

motor power

-@$QT7=& c. D~

and CL and cm are computed as before but me now’

C~Sd CLP and O.F

The coefficients for alI nacelIe positions at various

values of

~ ~d the ~went anglea of attack are

given in. Tables IV to VIU, inclusive: Table IV,

Thrust Co&icient (CT); Table V, Power Coefficient

(C.); Table VI, Propulsive Eilicienq- (II); Table VTL

Lift ~efficient with Prcpeuer operating (C..); Table

angles of attack of the airfoil were set within 6 minutes

of the desired angleswith an inclinometer. The motor

calibration showed a scattering of the points representing a maximum error of 1 per cent. The tachometer readings were accurate within 10 revolutions per

minute. The lift and drag were meaaured to the nemrest pound.

With certain nacelle positions at high anglea of

attack the forces fluctuated rapidly and the above

accuracy cculd not be obtained. This fluctuation was

particularly noticeable near the burble point of the

airfoil. The major portion of the faired results are

believed to be correct within +2 per cent, when the

scattering of the &t points and the accuracy of the

instruments are considered.
NACELLE COMEKUTA!ITONS IN V&IOUS POSITIONS WITH REFEREN~ TO WINGS . 663

1.4

1.2 -

Wing ofone

{

Sm’oll ‘–—— Exposed cylinders

ftmelle . .. . ... .. .. Vorioble ongle ring

—-- —-- A!A.CA. hod

---––-ALA.CA. cowhhg

1.0 “ P

/

<

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~ ● P

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-1- 0° - - -

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x +5° - “ -

A 10” - . “

❑ 12° - - .

0 .04 .08 .12 ./6 .20

c.

FIOUEE 13.-CompIrison oflift and dragcbmactmlstIcsfor wing aloneand

namllecombinationsinpmftfonB-l-A fah’edintowing

1.4

1.2

Wing olone

Small ———— Exposed cylinders

nocelle

“{

---------- Vorioble ongle ring

—.- —-- NA.C.A. hood

—–.-–- h!A.CA. cowling

J.O

/ p

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c.

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x +5” . “

A 10” “ - -

u , 12° - . .

0 .04 .08 ./2 .16 .20

.C.

FIOUUE 14.-Comprfson of llft ond dragcbmchWfcs forwing aloneand

P8calfecmnbfnatlons[n @tIon B, sidebraoketsremovwl

149900-3343

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r.o

~-k”

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//

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c.

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// {1 : -~. Angle of offock

. . .

.2 J‘ ;: ; x +5° - .-

JJ ii

A 10” - -- -

•1 12” - - -

0 -04 .08 .12 ‘– ./6 .:

c.

FIOUEE15.-Cemprison oflift and drag ebaraatarhtIcsfer wing elene and

necellewmbInationsin @tIon A-l-B, hired intowing

f.4

1.2

Wing oione

Smell ‘———— Exposed cylinders

nacelle. --------- Vorioble ongle ring

—-- —-- h!A.CA. hood

‘-–--–- A!A.CA. COWh~

1.0

/ <“

& .#--’

.8 A F

~ >

w

.A ~

c. / ./’

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~ 7:

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o -~. Angle of Mock .

-!- . . .

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x +5” . .

A 10° - - -

n 12” - - -

0 .04 .08 ./2 .16 .20

c.

FIOVBE16.–ComrerL$on ofliftanddrag cbm@aMm forwingahneond

nacdle combfnotfonsin @tion A->B
.- .. . . . .–-.—---- . . . .

664 RDPO13T NATIONAL ADVISORY COMMFITEE FOR AERONAUTICS

/.4

1.2

1.0

.8

c.

.6

.4

.2

0

i

------------ W7ng akme

— -/%%;:ed Exposed cylih&rs- —

. -—-—-— h!A.CA. hood

* ——.——- Ring 3, posifion 2

1

I 1 1 1

f

———— ExpLsed cyhndsrs

Nof _--—.._ A!A.CA. hood ~

- foid Ring 3, pmiiion 2

.

,

,

,

,

curve coincides wifh

curve for exfmsed

8’ cylin~rs, (fared).

I J 1 8

0 -5” Angle of offock

+ 0° - - -

d @ P

x +5° -

.

A 10° - - -

~ 12. . - -

.04 .08 ./2 .16 .20

CD

FImm.E17.-comfmrfsonof Ifft fold drag chmddmbfor wfngafoneond

nacdlecombfnotfonsfn rmftfonA-l-B showfngW* offafrfngfntowfm

/.4

--------- W~ ofme.

L2 — Fw>ed info wing

——–— Not fa-red

1,0 /

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6 0

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a , 12= - - “

o .04 -m “ .12 .16 .20

c.

Fmum I$.-Can_ of Ifftanddmg ~ of N. A. O. A.

cowfsdnscdle fn @tin B-l-A showingeffsctoffafrfngfntnwfng

1.4

1.2

Lo

.8

G

.6

.4

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0

I I ----~ ------- Wing o,bne

Side

,{,

.Exposed cy/;no’ers- —

brockets .— -—-— h!i:C.$ h~f; I

o~f ——-——. 9 , P. qz

.Side — —1——1

{

E@o.sed cyli~rs

_ brockei’s —-- —-— IVA.C.A. hood

on ——-——- Ring 3, posh’l~n 2 ‘

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❑

<’, /. &

/’ .

/H

<-

, “// / .

.

.’.

/

x

f/

/

,

0’// 7/ /,,

,) ‘Qf

o -5-A ngle of of tuck

+ 0° * - “

‘ @

x +5° - -

A 10” . “ “

n 12” m . “

.04 .08 .12 .16 .20

c.

FmuEE 19.-Oomrarbon of ffft and @ dwmtdstfca forwfng ofoneand

namflecombinationsfn IxMtfonB ShOWfJlL7OS?ectofs!debmokots

f. 4

1 ,

------------ Win olaoe

PAX7;qn WIt/? hood foirihg

f.2 — ———— Withouf hod folring—

l-i

{

I J ~,+J ho:d ~ai;,q I

Posifh

‘A-l-B —-—. .—. . Without hood folring—

1.0

& P

.

~ ..

.8

.0.

c.

.6 / *

,

,

,

/

/

.4 /

,’

: -Fe Ar@e of 0+tock

. . .

x +5” ● ● “

A 10” “ “ .

❑ /2” “ - “

o .04 .08 .12 .16 .20

c..

~GUBE XkOOmfmhn of fift and (h&! &uoctaMm for wfog atoneond

N. A. O. A. cowledna.cdfecnmbhmtfonfn PMtfona A-l-A ond A-1-B 8hOWfngoffwtofh dfafrfng
NACIMJLEl COMBINA!ITONS IN VARIOUS POSITIONS WITH RE FIIIUINCE TO WINGS - 665

DISCUSSION

A considemtion of the general problem of a nacelle

with a propeller operating in proximity to a wing

indicatea that several factom should be considered.

The nacelle and wing have mutual interferences which

appmr as changes in the lift and drag. The propeller

characteristics are influenced by the presence of the

wing and nacelle and the slipstream in turn changes

the forces on the wing and nacelle. A detailed discussion of these questions is given in reference 1, and it is

concluded that a comparison of the relative merits of

wing-nacelle-propeller combinations must include pro-

/.4

--------- Wing o/one

1.2 —–—— Ring 3, posifion 2

——-— Ring 3, posifion 3

—-——-Ring 1, pos!fion 2

-—–--Rin 1, position 3

— Vor7able cmgle ring

/.0

A -.

.

>’

,“

.8 #

.“ .’

c.

. / y

. /

,’ ,“

.6 .’ P

/

/

,.

,’

/

. Note:- Ring 3,. / ,

,’ 1)’

position 3 curve

#’ coincides wifh ring 3,

.4 Positim 2; likewise,

;’ ~?’ curves for ring I

,’ { ~coincide.

~ /, ~

1 1 8 t

o -5” Angle of otfock

.2

+ o“ - - -

‘ 1(4

x +5” - -

A IO” - “ -

a /2” “ - -

0 .04 .08 .12 ./6 .20

c.

FI13UBE21.*wfsOn Of Ifft ahd drag dmddstfcs for wfng aloneand

nnmflecomblmtionsin titfon B showfngeffectof cowlfngring~ and

pmftfon

pulsive efficiency, interference-drag effects, and lift

effects. A net efficiency is derived- therein which

includes the above factors in a rational and simple

manner. The same methods are employed here.

~TERFERENCE LIIT AND DRAG

Although the largest item in the net efficiency is the

propulsive efficiency, the interference-drag effects have

a large influence and a great deal may be learned from

m examination of lift and drag data from the tests

made without propeller.

Accordingly, these results. are”first discussed and

later the, propeller effects are included. Be&de simplifying the discussion, a clearer picture of the phe=

nomem is perhaps obtained. In Figurca 13 to 23 each

line represents a dMerent combination of nacelle and

/.4

--------- Winq olone 1.2 Postfibn B

–———mitim B- I-A

—- —-—ksiftin A- I-B

——-–Posifkm7 A-2-B

Lo

.8 .“ “.P /

.“ //

c.

/

.

,“ //

.6

.

.$? ,

/

,

/’

,’

.4 .’

,

,

,

;;

{’i

o-5° Angle of otfock

+ o“ - - -

.2 ~

!) ~

x +5” .

A 10” - . -

❑ f2” - - -

0 .04 .08 - .12 .16 .20

CD

FIGUSE Z2.-bnmn of lfft and drag clnmciarfsifcsof W@ alone and

_ ~~dw ~calle combinationfn fcaupodtfom

/.4

.

--------- Wing olcne

1.2 — Position B

–——— Posifian B- I-A

—- —-– Msh%n A- I-B

–--— --— Position A-2-B

1.0

/ & “

A

.8 .’ y/

~.:’;?

c.

.6 .2

.’

J >

.4

$

*

: -Fe Angle of offock

. . .

.2

i,’#l ; j;: ; ; :

0 .04 .08 .12 .16 ,20

- (3

~Q~E 23.-Comparison of ffft and drag &mrac&Mu of wfng aloneand

N. A. O. A. cmvhd nacalhcombfnatbnfn fcmr@tfons
666 REPORT NATIONAII ADVLSORY CO~13 FOR AERONAUMCS

COW& plOtti QS tL PO]SX di~g CL fi.@llSt CD With

the polar of the wing alone also given. The-abscissa

intercept between the wing-alone polar and that for

any wiug-nawille+mling combination represents the

drag added by the nacelle, i. e., the nacelle dmg plus

wing-nacelle interference drag. Similaxly,the ordinata

intercept represents the lift change due to the nacelle

and cowling. These intercepts are of fundamental

importance because the arrangement which develops

the least increase of drag (that polar closest tc the

wing-alone polar) is the best considering only the lift

and drag.

In Figure 13 which shows the results with nacelle

and cowlings in position B-l-A, at a lift coefficient

of 0.4 corresponding to 0° for the wing alone, the drag

added by the small naceUe with exposed engine cylindem is about four times that added by the completely cowled nacelle; that added by the N. A. C. A.

hood or variable-angle ring and the smaU naceUe

is about two and on-half times that added by the

completely cowled naceUe. These proportions hold

approximately at other angles of attack. The loss

of lift at a given angle of attack for the nacelle with

esposed engine cylindem is also to be noted. The

advantage of cow~~ is amply evident. Similar

conclusions are drawn from Figure 14 showing the

results for position B. h this position the nacelle

is partly within the wing so that the drr+gadded is not

so large. Nevertheless, the nacelle with exposed

cylinders adds about six times and variabh+angle ring

four times the drag of the completely cowled nacelle.

The loss of lift is again evident. The results for

positions A–l–B and A–2–B shown in Figures 15 and

16 are of the same character. The results for position

A–l–B (fig. 15) are especially interdng. Here the

cowling is not of so much advantage and this advantage disappears at the higher angles of attack. This

result confirms early flight tests on cowkd engine

nacelles made soon after the development of the

N. A. C. A. type of coding. In position A–2-B

where the nacelle is farther from the wing the cowling

is more useful but still loses its value at high anglw

of attack. In no case is cowling a detximent and in

the best nacelle position, position B, it is a decided

advantage, eliminating the loss of lift which occurs

when no cowling is used.

The results just discussed were obtained with the

nacelle faired into the wing except in position A–2-B.

Figure 17 indicatw the effect of the fairing giving the

results with and without fairing for position A–l–B.

Fairing between the nacelle and wing eliminates about

25 per cent of the drag added by the cowled nacelles.

On the nacelle without coding the fairing has no

effect. The air surrounding the nacelle is apparently

so stirred up by the engine cylinders that faking can

not smooth the flow. When the naceUe is above the

wing where the velocity is bigher the effects are even

more pronounced, as indicated in Figure 18. This

result was given in the tabular data of reference 1 but

is so stxik@ that it is reproduced as a curve here,

The drag due to the nacelle is reduced 75 per cent by

faking and this with the completely cowled nacelle in

both instances. The cases cited point to the necessity

of careful fairing when the nacelle is near the wing,

The gains are more pronounced above the wing than

below and with cowling than without.

Another interesting side light on fairings is given by

the re@ts of the teats with and without side brackets

on the nacelIe in position B. These me given in Figure

19. It appears that about half the drag due tc the

nacelle with hood is caused by these brackets. With

ring 3 and the uncowled nacelle very little gain is evident from removing the brackets. The most surprising

result is the improvement of lift. Where with side

brackets the lift at 10° was only 86 per cent of the lift

of the wing alone, with brackets removed it is 96 per

cent, nearly equal to the cowled nacelle and wing

combinations. This nacelle position shows the best

over-aU results, as will appear later, but the engine

must be cowled and aU protuberances eliminated for

best results.

A second variation of fairings is indicated in Figure

12, and the rcdts are given in Figure 20. It was

considered that the intersection between the hood over

the cylinders and the wing might produce unfavorable

titerference, and a fairing was placed over the front

as shown. The results indicate practically no effect

at 0° angle of attack and below, but at higher angli%

the fairing on the hood is a seriousdetrimentresulting

in large increases of drag as well as decreases of lift,

particularly in position A-l-A. This nacelle location

is poor on other grounds also (reference 1) and shotid

be avoided. Unfortunately, propeller tests were not

made with the fairing removed, so that the net results

for the completdy cowled nacde in these positions are

slightly poorer than they would have been with the

fairing removed.

The discussion thus far has been confined to general

interference effects, and no attempt has been made to

evaluate definitely. It is evident by now, however,

that the N. A. C. A. cowled nacelle is the best. The

N. A. C. A. hood applied to the small nacelle is better

thun the variable-angle ring. Although rings 1 and

3 do not give as good results as the other cowlings

tested, they do represent types strikingly similar to

cowlings that have been observed on a number of

airplanes. Although they are not recommended, the

results of some tests are given in Figure 21, where they

are compared to the variable-angle ring. Ring 3 is

slightly poorer thag the variable-amgle ring at low

angles, and ring 1 is p60rer throughout. This result

is perhaps accountid for by the cMerence in angle,

– 6.3° against –tin. Rings 1 and 3are circular,but the

variable-angle ring has nine sides and there is reason
NACELLE COM13~A!MONS IN VARIOUS POSITIONS WITH REFERENCE TO WINGS 667

to suppose it would be improved if made cirm&r also,

which could be done once the angle were tied. No

effect of changing the fore-and-aft position of the rings

is noted. The – 8° angle for the variable-angle ring

gives thelowest drag. Recent teats,however, on another

part of this project have indicated that the net efficiency is improved when the angle is made less. The

results of the teats of these rings me consequently only

useful aa indications of possible results. The alterations just indicated may improve the results,but it is

not likely that any ring on a d nacelle can be made

equal to a ring or hood on a large nacelle. Practical

considerations oftan dictati the simpler arrangement,

however.

As a final consideration of the interference part of

the problem, Figures 22 and 23 present the reauh%

from teats of the exposed cylinder nacelle and the

N. A. C. A. cowled nacelles in the various positione.

There is no reason why there should be any agreement

of results; but apparently the cowled-nacelle polars

follow an almost pdel course whereaa the uncowled

results indicate one position best at one angle of attack

and another at another. Position B is decidedly

better throughout with a completely cowled nacelle.

It is particularly poor at high angles with an uncowled

nacelle, Fair@ the completely cowled nacelle into

the wing, which showed such an improvement in

position B-l–B (@. 18), did not do this with the

uncowled nacelle except at low angles. The other

results are entirely in favor of the cowled nacelle,

although this advantage disappear to a large extent

at high angles of attack. This is, of course, to be

expected from the nature of the drag, the wing drag

increasing rapidly with angle of attack whereas the

drag added by the nacelle is substantially constant.

NET EFFICIENCY

The foregoing discussion represents the conclusions

that are arrived at without considering the propeller.

They are similar to what would result from any model

ksts where only the nacelle and wing were present.

The principal advantage of the present tests, however,

is the study of the effects of the operating propeller.

The propeller supplies the thrust necessary to pull the

airplane through the air and a proper determination of

the thrust available under any given conditions for the

diilerent nacelle-propeller-v&g combinations is the key

to the relative meriti,of the diiferent arrangements.

The variation of the lift and drag without propeller

has just been examined in detail. When the propeller

is operating, further changes occur and, in addition, the

propeller iEaflected by the presence of the nacelle and

wing.

These effects have been discuwed at length in reference 1and two factors are developed which are summed

up to give the net efficiency, a measure of the realmerit

]f any wing-nacelle-propeller combination.

l%e9e factors are:

(1) The propulsive efficiency representing the ratio

)f the effective thrust power to the motor power.

Effective thrust is detlned as the propeller thrust

minus the increase of drag due to the slipstream, so

that the effects of thp propeller on the body and the

body on the propeller are accountad for.

(2) The nacelle drag efficiency factor representing

the fraction of the motor power which is used in overcoming the drag and interference of the nacelle.

The. net efficiency, (1) minus (2), represents the

&action of the total motor power that is available for

overcoming the drag of other parts of the airplane

sxclusive of the nacelle. A high value of net efficiaucy

indicates a high propulshe efficiency or low nacelle

drag e@iency factor, or both. In any case the h&her

the value the better the arrangement.

The details of the derivation of these factom are

given in reference 1 and the resulting formulas only

are repeated here.

(T–AD) V CT V

Propulsive efficien~ = ~= ~ .G.D

c.c–c~ ~ v 3

()

Nacelle drag efficiency factor= ~” ~ ~=

P

Go-cm. s v 3

Net e%lciency= ~” ~~– ~p

P 0

Zz7im

where C%, drag codcient of the wing at a given angle

of attack.

C~c, drag codliciant of the wing-nacelle combination Q4the game lift co@ci.erd as the

wing alone, and the other symbols as

previously defined.

These formulas may be applied to any operating

condition, and if the conditions are fixed for all nacellepropeller-wing combinations, a direct comparison may

be made. Following the method of reference 1, the

factors have been computed for an angle of attack of

the wing alone of 0° (G!!= 0.409) and a propeller

~D= 0.65, corresponding to an assumed high-speed

operating condition, and also for an angle of attack

of the’fig ~one. of 6° (O&=0.652) ~d ~= 0.42, corresponding to climb The high-speed $is the average

value at which the propeller operated at peak eiiiciency

in the twts. The climb ~ is the corresponding average value obtained by assuminga climbing speed equal

to 60 per cent of the high speed and the motor power

reduced in proportion to the engine speed, i. e., the

engine developing constant torque, which is substan-
668 REIPORX’NATIONAL ADVT.SORY

tiid.lytrue for airplane engines. The lift effect ofthe

propeller is accounted for by adjusting “the angle of

attack to give the same lift as the wing alone as noted

in the definition of C% so that the comparisons are

essentially for the same speed, although the actual

speed is undetermined.

The factors thus derived for the gacelleaand cowlings.

in the different positio~ are given in Tablw IX and X

The corresponding data tim reference 1 are also given

for comparison.

Without going into great detail it is at once apparent

that the propeller has considerable influepce ?n the

final result. The eflect of the cowling on propulsive

efficiency i9 ii.rstnoted. In the high-speed condition

(Table IX) the N. A. C. A. cowkd nacelle gave the

least propulsive efficiency and ring 1 on the small

nacelle the highest. The propulsive ticiency with the

small nacelle unccnvledis also considerably higher than

with the N. A. C. A. cowled nacdle. These results

are in agyement with those of numerous other tests.

Apparently, bodies of high drag behind the propeller

give higher propulsive efficienciesthan low-drag bodiw.

k other words, the higher propeller efficiency partly

compensates for the drag of a poor body.

These fortunate chang~ of the propulsive eiliciency

are, however, insuilicient to produce higher net eiliciencim. In the case of the small nacelle uncowled and

with ring 1 the drag is very high so that the net result

is poorer than for the N. A. C. A. cowled nacelle in all

cases. It is of interest to note that the order of merit

for the diihrent positions is the mune as was derived

from the consideration of drag alone. This circumstance is considered merely fortuitous and it may be

said that the correct determination of the nacelle

location must include the propeller effects.

In the climb condition (Table X) the differences are,

as ~ected, lws marked. The propeller evidently

contmbutes a great deal, however, owing to the considerable vertical component of thrust and increase in

velocity over the wing. The nacelle @rag efficiency

factors are mainly negative, indicating a favorable

influence of nacelle and propellers. The same order

of merit obtains, however, as for high speed and the

use of cowling is of some advantage.

CONCLUSIONS

The following conclusions arebased on a general survey of the results of the tests. Other cmclusions might

COMMl&t’EE FOR AERONA~CS

be drawn, but would probably have to be modiiied for

other arrangements than those t-satedhere.

1. The drag and interference of nacelles are reduced

by cowling the nacelle. Cowled nacelles located near

the wing, however, should be carefully faired into the

~ ~fia tti supported by Stl’llts Ody.

2. Side brackets on nacellea ahead of the wing

should be avoided.

3. Fairing the cowling hood into the wing is to be

avoided.

4. The propulsive efficiency of nacelle-propellerwing combinations is reduced by adding cowlings to the

nacdle.

& The net efficiency is greatest”for a completely

cowled nacelle.

6. The best location of a tractor nacelle is about 26

per cent of the chord ahead of the leading edge of the

wing. To avoid a reduction in lift the nacelle should

be cowled.

7. The location of the nacelle and the type of cowling

are of great importance at high speed but are of little

importance at climbing speeds.

IIANGLEY lMmIorirAL bONAUT1cAL hoMTortY,

NATIONAL ADvrsoriY COm~EE FOR AERONAUTICS,

LANGLEY FIELD, VA., May 12, 195?%

REFERENCES

1. Wood, Donald H.: Teat.e of Naoelle-PropeWr Combinations

in Various Positions with R.&mime to Wings. Part 1.

Thick Win~N. A. C. A. Cowled Nacelle-~otor Propeller. T. R. NO. 415, N. A. C. A., 1932.

2. Weio!i, Fred E., and Wood, Donald H.: The Twenty-Foot

PropeIler Remaroh Tunnel of the National Advisory Committee for Aeronautics. T. R. .No. 300, N. A. C. A., 192S.

3. Weick, Fred E.: Working Chan% for the seleotion of Ahuninum Alloy Propelkm of a Standard Form to Operate with

Various Airoraft Engines and Bodies. T. R. No. 360,

N. A. C. A., 1930.

4. Wood, Donald H.: Tests of Large AirfoilE in the Propeller

Reaearoh Tunnel, Including ‘hVO with Corrugated Surfs-. T. R. No. 336, N. A. C. A., 1929.

5. Townend, H. C. H.: Ikduotfon of Drag of Radial Engines

. by the Attachment of Rings of Aerofoil Saotion, Irmluding

Interference Experiments of an Allied Nature, with Some

Further@)lfOatiOllS. 1%&M. No. 1267, British A. R. C.,

1929.
NAODLLE CO~INATIONS IN VtiOUS POSITIONS TVITH REFEREN CE TO lVINGS 669

TABLE I

LIFT COEFFICIENT WITHOUT PROPELLER

CL=%

Type of Cx3wllng &)m. p.h R. N.=.2Jb0,000 75 m.p.h. R. N.-3&T@ll Iool!Lp. h. R. N.4#X@ll

Ar@of atw-–.-.--...-. -.-..-.— –P w’ w lW –w o“ +& 10” –v o“ +-& 10” w

NomllepodtfonB, tie braoketsremoval

Nedfe pcdtion B, wftbtie braokets

Nadlo rmifdonB-l-A, fakedLutowfng

Nocelh positionB-l-A, nnfahed

NamEepmftienA-l-B, fah%dintowfng

Namlle @tfen A-l-B, nnfafm3

I

NamIIepmltlon A-l-A, fafrd Intowfng

N. L O. A. Mel: --------------------- ~~

N. A. O. A ma]----------------------

~~ M_& a~ :% ulJ a= 0.s73 : ;$J CL= :g 0-s76 am

.Sil

NamIle@tfon A-l-B, fdred fntowing

N. A. O. A. mwl L- . . . . . ..-. -------- a 16n

N. A. O. A. Mel----------------------- .lm

M& I 4a& 1:” ygII%:;4JM&agcLgam

wingalooe

a m a 417 aw am a175 a 414 am am a m a40a aw am am
._ ..L _.

670 REPORT NATIONAIJ ADVISORY CO~ E FOR AERONAUTICS

TABLE II

. DRAG COEFFICIENT ~THOUT PROPELLER

m ofCmdblg tclmp.k R. N.-2JtJ)@) 75m. p. b. R. N.-3&?2Il,COl liM m. p. h. R. h’.=4/S@J,@XI

Angle of-------------------------------------- –5” r +& w –P @ -l-b” 16= –r w +P w IP

Nemlla &tIon B, sidebmckatsramoved

i

ExPc&x3ohdm----------––. ---. -––.---—- aa326 W& :W& a ;6& :C& MS& :C& : :b& :C#& W& Cl@& : ;b& :;%

N. A. O. A- h&---------------------------- .m

~~m .&~t~n 3..____—_-___..------–– Rb13% titin 2-—------------------------ := := :g : ;~6 Jgg := ;= : ;gj := :~~ :~ : ;g$’j : ;~:

g ;$&~tim3._ ... . .. . .. . . :% %jl# :ljq :% :jg ;& ;% ju :~ :% :jg ;;% ;%

1, Pmition2---------------------------- .03!33

m –e----------------------------

N. A. O-A. Mel---------------------------- .G-m5 .0i40 .= -1533 .m .0423 .Um .1623 . 01Q5 .0420 . mo .1620 .1330

Namlle PJdtiOIlB, with atdebmokets

~ ay~d ---------------------------- O.aQo := CL= : ;07: : ~h cLc& acl&l : :&& a= llcl& :O&lj ~ :olJ ~ ;o&l

S N. A. O. A. ~------------------------------ .02S5

ti Ring 3, @tiOIl L.-.. ------— ---------------- .Cm3 .W23 .C@o . 16s3 .m .am . QM5 . 161b .0283 .ow .W-.z7 . NW .1910

Nacelle@tIan B-l-A, H Intowing

wtida...——----–-. -.-. --—–– a 0315 := CIQ& : ;o& := : ~~ :@Q&l a ;o& :@& CL@& cl= :;% 0.1026

S N-. A. hti-—------.–-. -..-. –------–– -m

6 ?%~e~mti~$:~;;:;~;=~=~~~~=~~~~~~~~ := :s :% ;;= :%& :% %J %J ;% :% :~o :;; :;;

. Iwo

N. A. O. A. -L. — . . ..-. --–------. -.–-–.-.-.---– .0z20 .m .W

NamUetitian B-1-A, nmfdred

N. A. O. k Mel-. ---.. -.–--.---––.----. -.--. -.–.– &oao 0.- am a 1796 0.azm aw a 1070 a 1776 am o.W5 a mo a 1740 0.’2WJ

NamIle&tinn A-l-B, falredtntowing

tida ------------------------- 0.0!40 a 0576 a QJM : ;4& := :O& : W& : ;4g :C&l :~ :@& ~;% :;%

2 g%%. A hti------------------------------ :% : ~o .-

~ ~~&@&~?;~.::::---------:::::::::::: .@t&Kj := :&# %J %J :3 :% ; ;%J %& XJ ;~ ; f~ ; :2

N.A. O. A. muL---------------------------- .omo

NamIleweitim A-l-B, nnfahwl

ExIK8&3whd~-------------------------- ao44b &c&z a C@16 : :g cL~ :@& :09& : ;~47 : g: ~ w& a GW6 : ;$77 : ;~o

z N. A. O. A. ha----------------------------- .U370 SB& := .a3s7

& Ring& @tin k.-. ------. -.-.. –-.. -... ---–– .0!4s .1510 .04m .a502 .0910 . 14J) .04a3 .0660 .Wm7 . 14ea ,1740

Na@a podtionA-2-B

EXWCWIowdm --------------------------- am aw a-ma :;% :c@& ~O& CIM&l: & cl~ cl@&tJclcm&::% ams

z N. A. O. A. bd---.-—.------. -.----–. -.-..– .@40 ;&2j :~ .1700

Rln 3 padtlon2-------------------------- .C837

; Va&.b}erfng ---------------------------- .Cc36 -O&n .Wo :%! %J+# :~ :g : ‘H ;% ;% jg ;:% : ;fl

T. A. O. A. -L----------------------------------- .0246 .Cnb6 .Cs2J5 .1410

NacellepmitlanA-l-A, fairwlintowing

i. A. O. A. -Lo. -–.-... –.––.-.–.-----------.–– am a 0547 := a&e as : L-m: CL% :;% llc# := 11~ : ;O# a IWI

~. A. O. A. -1---------------------------------- .0200 .Cum . 2m.s

NamIl@ @tIon A-l-B, W intowing

T.A. O. A. wL1-------------------------- am ao476 am a 1426: pa yOi& cm& : ;4$ CLClg cl~ IL= : ;;;: 0410W

? A O A. Mel----. --–-. –.––.-.-.-..–-----–— .UM1 . Olm .m -1570 . 18PI

mug alone

am am aam a 1440 (t0176 CLML5 am 0.1440 a OMJ aow aw a 1440 a 1740

1Nm fahingl’12JD0Vd.

.
NACELLE COMBINATIONS IN VARIOUS POSITIONS WITH REFDR13NCE TO ~GIS

TABLE III

MOMENT COEFFICIENT WITHOUT PROPELLER

~ = Moment

.

qsc

(Afomont9werethemmeat aIlafrepwln)

I ‘of- m

NomllepmltionB, eldebmoketsofl

fWcelle pcdion B, withsfdebreakata

1

-d M*- ------------------------------- -a 077 –: ~ -a m –0. am -a w S N. A. O.Y. M:-------------------------------- _-m–. 076

ti

–. oM –. am –. om

Mug 3, POsitfonL------------------------------- –. am –. 0.51 –. 0s9 –. 018

t

I

Nacelfepdtlen B-1-A fak’d fntati

1

~

~d~--------------------------------- –-g -’ g ~g –: ~ -’ ~

2 gA. a.zhti ----------------------------------

; &%i$’ring-8°

tition~--------------------------------- –. am –. m –. O-fo –. M –. m

--. --- . . . . . . . . .. —--------------- –. w –. 04s –. 046 –. M –. w

o. A. mug-------.. ——----------------------- –. 061 –. 0i4 –. 040 –. 043 –. 043

I

Nadle Pdhl B-I-A) nnfdred

N. A. O. A. ----------------------------------- –a 031 -o. m –Q w –a 04s –a oi7

NamIlepcsltionA-1-B, fafredfnti wing

1

~ == ~~

Ex@ed Mb-------------------------------- –fL076

Z N.& O.~. h&... --.--------. - . . . . . ..-.. -.--.l..

~ R~3@timL -------------------------------

V b~e@-@---------------------------------

N. .0. A. mhe--------------------------------

NacellepasltfonA-1-B, nnffdti

Expmed ~~.--— ---------------------- –a m

z N. A. O.~. ha----------------------------------

–o. 071 –a w –_a ~ –o. 078

–. 078 :%4 –. 070 –. 076

G Rfng 3, pdtlon 2---------------------------------- –. w –. 074 –. 076 –. 07s

NacelfepesitfonA-2-B

671

I

z %%.%s::::::::::::::::::::::::::::::

Rfn 3 tition~---------------------------------

-MJ --# -:- ---g -:%

;.L\+\&cd-:... .. . .. .. ... .. ... .. ... .. .. .. ....- . ;. –. 074 –. 075 –. 076 –. 074

. . .--. .--. - .. ..-. -. —--------------- . –. 071 –. m –. 07u –. 070

.
._ ..- -p. .-. — ..+. —.. -

672 REPORT NATIONAL cohrmTrEE

TABLE IV .

FOR AERONAUTICS

THRUST COEFFICIENT

cl= ~

PropeIk No. 441Z-4 fe@L Sat 17’ at 0.761?. Angle of attack--~

v

iii

Typ30f0.1 62

I

03 0.4 a5 I

0.6 Ia7 0..9 0.9 1.0

Nacelle @tion B, sidebracketsrammed

O.aw

.Cwl

.C@s

.m

.C&i5

.@72

.mw

.(M2

0.K23

.am

.W6

.Cs18

.=

.U339

.Ce43

.Cm5

: p’&

. ml

.0760

.0i73

%J

am

:E

.W7

.Oim

.0n2

.C897

.03$5

ao-5s-9

.0s72

.0597

:%!! .0623

%%

a gg

.Ws9

.OMa

.Ci5z2

.a524

.W3

.0w3

Wcalle PMtion B, with sida bnwkats

cLo3&

.CeJ37

.CGT3

.6ioo

.04a

.am

.0339

a a319

.0196

.(EM

XQ#

.0276

.a247

.m

(lmim

.mo

.m61

. Olw

. ON

.0123

.0101

.lX&l

-a m74

-. Olwl

-. B39

-. w

:. ~o

-. ms7

–. o116

Bsmmedcylinders------------ ~~ aa3n

z N. A. O. A. had__________

a 07m aw ao5s5 a o176

. Q311

a am

.0751

a aaM \&o -am

. m74 .W

05

.62U3

R~ & @tIon L–-.-..-... .W .@X1 . 074a .0370 :% .64S3

–. m

:%& .O.ul .m -. K@3

Nacdb &tion B-I-A, fahd Inio WQ

Nacdle pMtion B-l-.&nnfahad

N. L o. L cmhg_________ aam aom ams am aom aw aam am am -0.0110

Nacalle@tIon A-l-B, H intowbkg

lhpawi Linden---------------- amw cLms& ~~ acw aow % N. L 0.%. hmd---------- .m

~ Rf&\j@ition 2__________ S&zJ SJ7& , :% $&J %!J %J ag a~o ag -:2

V b rM-&___________

N. A. O. A wwlin&---------- .aX15 . 07w .07W .W36 .Gi8 .0146 .a?m .Wll .m -. alrl

Nnmlle@tIon A-1-B, anfnbwl

ders--------- 11~

% m.%m.d----------

:Oz& ao737 Qg acrss :O#& aa clccz&

.07m .W45

a 0123 -am

G Rhw % *tIon 2----------- .aEa .0i87 .07?3 .mm

.=7 .0)73 -, m

.a570 .04!53 .am .W42 . Olla -. ~16

NacallapasitlonA-2-B

J

Exwsad llnda%---------- a@& aasm

ti N. A. O.T h&__________ a ml aoiz acma . ME? .aE13 .0x7 .0074 &&

: :%a,mmti:%kz::::::::::: ---xiw- ---:g- ---;g-- -jg-- --%J- ---;g-- ---;g-- ---;g-- ---;;-- ---:~xiJ”

a.A.cOWhg______ .C655
NACELLE COMBINATIONS IN VARIOUS POSITIONS TKtTH REIF331U3N(IQ TO ~GS

TABLE IV—Continued

THRUST COEFFICIENT

CT.!*)

Pre@er No. ~ fret. M 1P at 0.76R. Angle ofettwk-~

v

a

Type of mc!aIfe

0.1 0.1 0.3 0.4 a6 0.6 , 0.7

I

0.8

I

0.9 1.0

Necedfe wftfon B, sfde braokeb WOOVd

~

1

E- Binders----------- a 0743 am :tW&l :~

N. A. 0.’% hood_ .-—.–.__.- %% %% .0723 .CB48

a ml o.Olw RC054 –: ~

j

E*~&ii~-_----_

:g :% :g~ := := :O& ;% :% ;#?J ~%

—--. -.. --. —

- -.--.—.—. . aM9 . lW16 .0706 .W37 . Mlo .W03 .ma4 .CQ61 . mm

Rin 1 pxltion 3__________ .aM9 := .0713

–. W.o

m vo+bmtih;8:-------------- -w .* -m -w

.&m IO& .02s

. C376 :%% . IW4

.0110

%J

-. w

N.A. .

.0474 .02W .KF31 –. W78

-. -.——.-.—— .04M .m!28 . Olw .W5z –. O11o

Nmxillepasftion B, wfth sfdebrackets

g

KY% TR’’-:::::::::::

d Efng 3, pmklon l-.-_ .—__— a%! :%! a%! a%! a%! %% :% :!% a!% ‘%?!

NacaIle @tfon E1-Aj W fnto wfng

Erposei Under ---------------- o.m57

z N. .L C.~ lmod_._-.__..__– .C@51

0.mlo 0.0747 am am o.W8 ~~ O.ai%a

. a313

a am –_yg

.0748 .0s6% .cml .m

:W :W

; ~va%~~~LP__-_.-.-.--.-. J& :% %J %J := A’& %J’ %$J ;% :g

R 3 pmitlon 2_________ .Wiz .W7

. . -. —.--- .-. —---

NacaIle @tIon B-l-A, unhired

N. A. O. A. WWh18--------------- O.U323 a 0707 am acw2 a (WI aom a a314 a 0186 aoo44 -0.0110

NacaIfe pmftfon A-l-B, fdrd fnto wfng

L

~ EIPUWI O Udders---------------- aaw acj.1#

. N. A. O. ~. hood-. -... -.---– S&

a 0742 (L3&l a 5331 a oi74 aa366 aw :kg

.0n3

-_: %5

.W61 .0469 . a367 . CQ47

;. %’$W%iiET::::_:;E: :% iii :% :%? M %! :!%! %! %% xi

Namlle ~tfon A-l-B, nnfafmd

2

ExPM&3 @riders-. -_- . . . .._ aowa 0.0776 aom amw aw 0.0473 cLO# a $4:

N. A. O. A hood-------------- .m .0703 .0703 .03W .as46

a 0118 -am

.0462

m“

.0110 –: ~

Ring 3, pmitfon 2..-. -.- . . . . ..-. .aEa .0780 .0720 . W-47 .asm .W .m .0254 .0133

NacallepcaftfonA-2-B

I

Under.-.-. ..--. . . . . aam7 am am cl@& ams 0:$&

~ E%%% hmd___________ @& m?& :%

a oilo aam a 0131

.Wa

-_: &3

ni Bfn 3 pmitfonl---------------

Var&b&bw -&’----------- ;@& .W .m

.0714 .mzo .am .m83 –. m

.0710 . m14 . am

N.

. CQ75 –. ml

.0. A. .X!Wti&----------- . a313 .0760 .m . @576 .0ie4 .m –. Olra

673

/
——.— ——— ., _.._ ..- .—.— ...— -. Ji .

674 RDPORT NATIONAL ADVISORY CO~ FOR AJ3RONAUTICS

TABLE IV—Continued

THRUST COEFFICIENT

Prqmlfer No. 4424 fek Set 1P at 0.75R. Angle of atta&-+lF

v

ni

Type ofnacdle

0.1 03 0.3 0.4 0.5 0.6 0.7 0.8

I

0.9 LO

NaceIfe pmftfon B, sfdabreckats ramoved

~

1

—

Ii

E?q)md oylfnders..._____ . ...- aam a om3 afnm ~~ :&4 a ~8 a amI a oma ~~ -a w

N. A. O. A. hood __.__ ._.-._. .0322

= R@% IKGitfon2----------------- :=

.0769 . 07Q3 .WJ32 .0174 -.0113

.0759 .Wa3 :% :~ .042J1 .am

Ring 3, pmftbn 3_ .. _________

.0192 := -. W76

. 07a) .W32 .M26 .0317 .0197

Rfng 1,~tfon 2____________ .C#3

-. W73

~ %%b}.

.076s .0712 .m .Wi49 .0449 .m40 .0221 .m92

o.A:rg3~~~~~~~~~~~~:=:

:~ :% :WJ %J ;~ :~ $# ;~$ ;~ ;.

-. w

----------------_-

Nacalle PMtfon B, wfth sfde brackata

~ Em@ed @fnder6___________ a cm MJ7# a rim a W14 a 0517

N. A. O. A. hood _._. _.._. ___ . a315

a MO aw

. Om

a 0177 ;% -a m

05

. m24 J&l .04!n .03m .0176 -. Olin-l

B~ 3, ~tion 2_-___--–––-

-~

. 07ES .oim .0120 .0434 .fmza .Qm3 . m72 –. W.o

NacaIfe wltfan E-1-A, W fnt.owfn8

.[

~ ~dm---------------- am46 aom + N. A, O.% hti_________ a mm : p; II= :%

. W6

a fm a 0197 aw -a 0070

.0762 :~

; %%W%%i:.s%=II:::IEI :E :% :% :K$J :Ii$J ;% %!J ii!! ;g ;j!j

O. A. was_________ .aW1

NoceUe pmftion E-l-ii, unfafmd

N. A. O. A. @mWnG_________ aa3a3 0.0751 a 0s31 aowu am o.C-fo4 0.0204 0.Olm am –o. 0102

Nacelle pmitfon A-l-B, fafred fnte wfng

.

Eqxed landers___________ a m24

z N. A. 0.%. hc-ni__________ .W07

a 0774 a 0712 awo aw a 0471 aa379 0.0279 a 0176 0.m

~ :~~~w~~~--------------- J# :% :% %J %J :% :HiJ :% ;%, :%

----- —.-. —-. .—

N. A. O. A. mwlfng___________ .07e6 .0775 .U399 .W.27 .W .C437 .a336 .0231 .0123 .W15

Nedle w[tfon A-l-B, nnhfrwi

E- oylfndera–_________ amm

2 N. A. C. A. had__________ .07w3

a07s4 aom aom awo aoim afrm

.0747 .CW.o .Cml

a 0M3 Cl&l

&

.fm2 IO& %g S& .0116

Rfng & pmftion2---------- . mlo . 07@3 .W%3 . MM .asia .0146 ,MEa

Nae@ pmftfonA-2-B

Equeal cylinders-___._._–_ am7 am aom7

s N. A. O. A. ham__________ .@34 .W

a Q713 a M21 aa520 ao404 aomo 0.0149 aw

. m4 .W7 .m .WW .m ;= .0129 -. m16

m %W%p’ill:::::::=: :%% %# :~ %Jj :% ;MJ %%J :~ :y# _:yj

N. A. C. A. caWn~__________ .m54

\
NACELLE COMBINATIONS IN VARIOUS POSITIONS WITH RDFERENCE TO TVTNGS

TABLE IV-Continued

THRUST COEFFICIENT

~== (T-AD)

P n2LY

PropeIler No. ~ feak SetW at 0.76R. Angle of attack.+1~

v

m

Typ3 cdrmalfe

al 0.2

I

a3

I

a4 CL5 ~ 0.6 a7 0.8

NecaIletitbn B, side braokek removed 4

I

0.9 1.0

a 0a31

.aL53

.W&5

.W8s

.am

.Olcm

.m79

.aM1

-a m

–. CI)7b

–.mm

–.03s3

–.W6

–.ms

:.$@&

Em lfndors------------ amm

2 N.& 0.% heed ___________

0.0740 au970 aom Uom

. 07s3

a 6401 uoza9 a Olw arI# -a m

. Oza .0963 .0570 .0475 .U373 :~ .0151

Oi Ring 3, fxdftion 2__________ .679s .0740 .M-$9 . 0s31 .6s4

–. m

. msl .0161 . ml ~ Wn

NmJfe @tfon B-l-A, fehwi fnto wfng

aa333

2 :m.”~?:mc:;::::;:::::::: .0796

a&a a 0678 aw am aozo aozm

.@394 .0670 ;%

Qi Rln 3 pmltion 2- .. .. .. .. .. ... ...

.0376 :%

Vrr&b\e ring –8”___________

. osll .0740 .W.9a .0s78 .mm

. awl .0747

N.& O. A mw~g—.-.--------------: .07e8

; %6 :g .64%3 ;= ;%

. Om .6401

Nmnlle @tIon B-l-A, nnfehwl

I

a u~

. OIM

.0161

. Olm

675

O.mzo -0. olw

.m -:0132

.m –. m

–. @s

–: w –. Olm

N. A. O. A. mw~...---.---.-------.- 0.0776 sons

I’wlaml aw’llamlamlao+-aml

–o.0143 ,

NecalfeposftlenA-l-B, felral fntowins I

Em o ffndars.._ . .. ...___. am

2 N.& O. K hood _.____ . .. ...-

a 0748 awu am

.on% .owl .0040

0.0616

.04sl

aw aam aoriw

1-

ao141 arm

.rtw .am

M $%;~a%tif$.-.-.-;--~;;;;;=;;;; :% :)5 :E

:%% :E Jr& .0242

.0118

.Wlo

.W17

. 014s .Mwl

N. L O. A. WW~— ------------------ ---------- ---------- ---------- -..!’?!-. ---:!!! --.--:!!!-!-- ------–– .-.:!!!!-. ..-!?!-– -.-.:!!!--

Namlle @tfen A-l-B, nmfeimd I
— —.-— . . . . .... + --- —— ~=..—- A.- - -

676 REPORT NATIONAL ADVISORY COMMITTEH FOR AEEONA~CS

TABLE V.—POWEFL COEFFICIENT

Pro@er No. ~fmL @@tl~at O.76R. Ang.leof8tteak. -fF

v

nii

l’gpeofnasene

0.1

I

ccl

I

a3 0.4 0.6

I

ae 0.7 0.8 0.9

I

LO

f

Nacelle WSItion B, side brmkets removed

=nc@ oYugd&__———

12———-.-=

13——______

CL04M

.Oils

.Om.l

:%

%%

.CM2s

aoa

.mll

%&J

.mlo

.mm

.0410

NamIle WSUIm B, with side

lLo3& nag

.mm .M50

.m89 :~

.Ca96

.mm

:%%

:%% .aM3

breckets

am

.Ma5

.0313

. MM

.0311

.a317

.M24

.m

MU& :&g

.0239 .0140

.Cr240 .0140

. mm

:E9 .0165

.Ozm Al#

.0?27

.; &j

.m.W40

.Wio .

-: %!

1

Nedle IX8Mon B-l-& k !

N. L O. A. cnwlhM————___—— 0.0426 am23 a m19 O.(J4U Q.M93 a@ll ao31!a aam a o13a a au

Nerd.lePU$tienA-l-B, Mred intoWiIW I

Nn@e pmltion A-l-B I
NACELLE COMBINATIONS IN VARIOUS POSITIONS WITH RIOFElRJ3NCIil TO TVINGS

TABLE V.—POWER COEl?FICIENT-Continued

Cp=m+

mer No. U-4 feak E@ 1P at 0.7si?. AI@ of attack -F

v

a

Type of nacene

0.1 0.!2 03 0,4 0..5 0.6 0.7 as 0.9 LO

NaceIle pcaitfon B, sfde bmokatYrsmovwl

1

$ $m ~~dem.._..-- ....-

h@xl_____ .__.,

a Ring a, ixr3ftfon2----.. _...._-,

~ ~~r#f0n3- — .-—------

tfon 2–-.-...___-

; :%60%F:P?::::::::::::

o. A. cnmlfng______ ----------

0.Ofm

.0428

.0434

.0441

.04%7

.W3

:8%

a 0431 11~

.0425

.04?3 :~

:@ .0424

.0431 .04m

.0434 .04M

.0423 .041.9

0.04L5

.0410

. MM

.04m

. CU6

.04m

.0417

.04m

0.0301 UCW4

.03%0 .mm

.0395 .03s

.0407 .am

.0397 .mm

.am .mos

.am .mm

.am moo

a ml

.ama

.am

. aus

. CQ17

. CL318

.mm

.am5 7

Lu2&

.0237

.0239

.W449

.0249

.024s

.ano

a 01s0

.0116

.0137

-.0140

.0169

. Olm

. Olm

. OEM

O.(Km

–. mls

. Wlo

. mls

.W

.m43

–: E

o.m14 Q.0240 0.0137 0.Ix04

.mm .0z7 . Ol!m

.m .mm

.mxl

. Om . W16

N. A. O. A. wwlfnL.--..-__.._ ao425 ao423 11o419 0.0L09 O.CIm O,- O.m ~~ 0.0137 0.ml

Nacelle @tfon A-l-B, fefrwl fnto W@

!2 Eqxsed lfndera___________ 0.0440

d

N. A. 0.% htxuL_..___ . .. ..- .04m

Rfn 3 IXISItian2_.-__ -_ . .. ... .W43

V~bie~ –80------------- .04m

N. A. O. A. cowlfnK-._.._- .. .. ... .. . .0s

NaceJlepasltfon A%-B

awo ao43s aoua o.m

.C446 .0423

0.m74 := am a 01ss O.w

.0442 :@ .Cuz4

.am .Oxa

:W :% .am .Cu.sl

.0100 .Cu35

.0447

. ohm . m45

:%! .0433 :E

.0m7 .02s7

:% . ml .am .mm

. Olm

.01S2 :%

677
.. ...- ..-, . .... ... . . . .- ...-

678 REPORT NATIONAL ADTISORY COMMTIT’E E FOR K13RONAUTICS

TABLE V.—POTVER COEFFICIENT-tintiuti

Pm@ler No. ~ feat. Set IT at 0.75R. AI@ Ofa~-+~

v

=

TYP of nwaIle

0.1 a2 a3 0-4 0.6 0.6 0.7 03 0.9 1.0

O.c-w

.M37

.0437

.0434

.0$34

.0434

.0i40

.CMM

11.M32

.0!30

.0J30

-:8%

.Owl

.0423

.M2f

0.0U6

. fu17

.0416

.fuza

.M20

.Oul

. oils

. Om

O.am

. .f@6

.aw

.a390

.am

.mQa

.0396

.mw

O.w

.CB-57

. ma

IO&

.am

awl

.mm

Lla#

. ml

.:=

. fG16

. mlo

. frms

o.m .0. &l -a Cm3

.am -. am

.am .0136 . ciu6

.0233 ; yg .Mtz3

.0240 . CU37

.0245 .0164 . ciu6

.022a .0146

. ml .0120 -: E

Namlle wuftfon B, with.ddebmok@is

i

g ~ ~d~---------------- a~ o :g 0:g : ~6 :=

N. A. O.~ hind------------- .012S

a- Rfng & pmitIm 2___________ .0439 .0$37 .0S0 .Win -m

~ag a= a%

Nudle rmitien B-l-A, fahwl fnto wfnK

I ,

a 0447 UW42 am aw

.m .om .oln .o’m

.ow .W mZ& .W

:g m& ;=

.wu

I I 1

Nmallo Pmition B-l-A, nnfafmd

o.fe.69 a a315

.fcas . a311

.13371 . a319

.fuJI .fnm

.C8E3 .m

acrm a013s 0.CD)14

.G234 .0132 .CQ3s

.0244 .0146 .m!is

.0i32 . 01Z9

.0az2 .0119 -: l%

N. A. C. A wwlfn%—-–---––––. –.–– O-W 0-= o.~ am a- a~ o-~ 0.~ 0.0123 aom

NwaIle pmitfen A-l-B, fefred fnto whm

awn a CU16 a fua3 am

.Cu27 .0iL3 .0404 :=

.0423 .0117 .0m2

.0s2 -w .Oul

.13M . oi14 .Otm :%%

aaw aom ‘am a 0114

.m4.5 afrzas :% .0110

.W2 .oim . Olu

.m60 .0292 . 02f2 .0113

.fesa .0% .02a3 .0116
NACELLE COMBII?ATZONS IN VARIOUS POSITIONS ~ REFERENCE TO TVTNGS -

TABLE V.—POWER COOEFFICIENT-Continud

Cp”m+

Prcwllar No. W-4 feat. Set 17’ at 0.76R. Anglo of eAtuk=+l@.

I v,

Typa on nacelh

n

0.1 a2 0.8 0.4 as . 0.6 a7 a8

I

0.9 Lo

Nacalle @tIon B, aidebractets ramovwl

11ExP@xI oyUndam... .. .. ... ... .. 0-6433 O.OCB ~~

$ N. A. O. A. hwi- . . ... ----------- .64Z3 .0423

j #M!%!%::::::: i%

,% :~

.0434 :~

m 1 @tIon 3-.. - . ...-. -..-... .0424 :%

Varkbie @–S” ----------------- .6448

N.

.6443

.0. A. mwhg. —----------------- .642s .6422 .0418

(l% a 0397 am := o.H : pJ

.03m :~ .-.

.6t17 .aM9 .0317 .w? .0152

.0403 :~ .0324

:%

.0160

. 6iol .m :$% . 016s

. MM .6369 .W

.0431

. OIFS

.0410 :$!% :% :% .0167

.64M .m .- .m .0131

Nacslla &tIon B, with side bradmti

0.W18

.W

.@

.6645

.W6

.m

.D35

. a117

EILKUMI Undaru... . .. .. .. .. .. .. 0.0M3 0.0446 0.0442 0.6424

2 N. A. O.% bum-:_.._..._..–. .6437 .0438 A@ :~

o.04@ 0:~4 0.6D4 a= 0.0160 O.w

Ui

.m

:%x .(ES3

. 013s .m

Ring 3, pdtton 2 ----------------.0L?3 .WJ3 .a312 .0242 .01s3 .W43

Nacalla @tIon B-l-& fafrwl Into wing

Emomm....------------- 0.0445 0.w? 11~ O.w o.C410 0.0376 0.w o.a2Kl

z N. A. O. A, hmi-.-..-...- .. .. ..- :% .M43 .W .W :g -m

o.01s0 0.W27

.mrd .mlo :~ ;:)

m ?%b%@@ti-%2.:::::::::::::=:: ~~ :%

.042s .ml?

.0426 . OiM

:E

N. A. O. A. mwtig --------------------

.m :g

:&

.0140

. oi17 .C@3 :% .m .0116 –: w

Nacalla p.%ition B-l-A, tmfabed

N.A. O. A. MWbL -------------------- &w O.owd 0.0416 ao404 am 0.0362 0.Ur2 am a o124 am

NacaIfe posltian A-l-B, fairwi into wing

ExP@M Wbdw ----------------- :% aw 0.6420 :=

z N. A. O. A. baxf_.._ .. ...__. --

0.0411 am 0.0362 : MO :g a 0145

M

;%:b%~$.:::::::::::::::::

.~= j~ :% :~ :% ;~ ;% := := :%

N.A. O. A.@Jw~------------------ :% .- -Ml .047 .~ -~ .- .c013 .W40 .0147

Nacalla position A-l-B, nnfaimd

ExP@xI otidm ----------------- 0.64M 0.6436 := :~

Zi N. A. O. A. bad------------------ .0s37

II Mll O.amo 0.W14 :g := R o146

m.

.6th .63s7 .W

:% .04sa .W

; :1

Rfng 3, pmition 2---------------- .6435 #M16 .W .mm .mll .0242

Nncalla @tIon A-2-B

Oywm ----------------- aoi40 :M& CLw 0.0s3 Cm&

% :%’%.A. hti-...-...------.-- .04s6 . C447 .6428

m“ Rin 3 Mtion 2----------------- .0447 ;=

Variib~e ring-------------------- .6453

.0447 .64s9 :=

.0452 .0443

N. A. O. .L WWhQ ------------------- .6437 .0439 .M.M .~ . MO

—.

0.0123

.Olal

.0140

.0123

.0110

679

149900—3~
———-—.-— — ---- ..

680 “ “ REPORT NATIONAI.J ADTT.SORY COMMTITDE FOE AERONAUTICS

TABLE VL—PROPULSIVE EFFICIENCY

Propelfer No. 4412-4 feeL Set 1P at 0.75R. AI@ of attak–-5”

v

Tyfm ofnacsne

?ii

al Oa as 0.4

I

an 0.6 0.7 0.8 a9 1.0

—

NacaIle wskfon B, side braoki

~ oylfndei—s__ -. ——------ am o. w a= sobs

N. L O. A. hind—---— ------ .m ..?s0 .s29

R@% fxsftton L._–.-––.-

.047

. 1’2s

~: x#~ ~_--_..–

.3s3 .H2 .070

.196 .372 -OJ, .W4

—.-. -. ———--

V%Xhe”~X$-----------

;g :x ;g :JJ

——---. --_-. —

.0. L cowling__________ -m .Ssl .m .049

removed

a 746 0.799 a pl

.722 .706

. 7@3 :&s .8!M

. 7KI .s29

.m .Ma .am

.Sm .s70 .SOI

.764 .W4 .ml

.731 .m .782

a 706

.@@

.783

.WJ7

.E04

.s94

.m

.736

U.&

.etu

:%

.731

.EM

.m

....... . .

...........

..-.-.---,

. .........

..........-

... ..... .

......... .

...........

Nadle pmition B, wfth tide biwkets

ii :yf$oy~&-:::--:::: ?% a 374 a5a3 :%1

.275

1

a 744 u39 as35 : RI CL% .. .. .. .. ..-

.KM .730 .m .=

m“ Mug titfon 2--— _______ -

&

.. .. .. ... ..

—. —.- ——-—-— .. -----— ——————.-...—. .. --—-- --------- ---------- ... .. ... .. . . .. .. ... ..

1?.A.v%li %iigz-x::-xz::

.lw . a74 .s29 .053 .752 .SQa .&30 .794

.193

.001 . . ... .. ...-

. S76 .m .051 .m .m .7W .740 .447 .. .. .. ...-

Nacalfepdtfon B-l-A, anfelmd

N. A. C. A. @3W~Q -------------- aw am 0.614 aou a 701 a 745 a 7M a e!! a430 ---------

Na@elle@tfon A-1-B, H intoWQ

Exfmed aylfndars-------- . Ol!ai am a 614 ;g aow

z N. ~ (J. A. ~_________ JfrJ .aezl .m

a 724 :% ,awo IM3J .. .. .. .. .. .

rdtfon ~--l -----------

.m . no .Im5

; %%e Rfng –P_________ ;%

.61J .046 .7Q3

.. ... . .. ..-

. 8U

:E :%? .@6 .W

. 7s1

.497 .Sm

. ml .. .. .. ... . .

A. o. A. CnMfng----------------

. a4 .4M .. .. .. .. ..-

.Ml .494 .eO1 .6s3 .721 .ns .093 .4M ----------

NamIle pdtfon A-l-B, nnfafrd

oylbMMa__________

z F?%%. A- hJM__________

a 191 cl% a 614 a% a 781 flg ~g a 767 aoo5 .. .. .. .. .. .

~ Rlmz %titfon L.__-._--—

. 1s6 .4s3 .0s4

. M .%53

.m

.W1 .019 .70.5

.376 .. . .. . .. ..-

. 7W .7% .726 . b71 ...........

.—

Namlfe &tion A-2-B

S :=. yiyi$i$--:-::::z:-_Yv% %%% % :% a w a8.59 a ft21 a 40s ... .. .. .. ..

.770 .759 .234 .. ... ... .. ..

~tfon 2__--__.––– .-–:iti-. ----.–E.. --:.:EK ...-.ti_ __:=. - .-..:%.. –.-:=-. ._l;.. .. ...%.- ~:.-.:.: -..

m %i%e rfng -W—.___-.._

N. A. o. L mwlfng-._-____-_— .M4 .2-s3 .516 .esl .m .770 .771

. . .. . ...

.076 .lm .... .. . ... ..
NAC13LLE

.

COMJHNMHONS IN VARIOUS POSITIONS WITH REFERENCE TO WINGS

TABLE W.—PROPULSIVE EFFICIENCY-Continued

,,_ (T–py v

.

Pre@ler No. 442-4 feet. Set 1P at &7bR Angleofattac&-@

v

TYPO of nacelle ni

al 02 0.3 0.4 0.5 M 0.7 I Id’o Oa

I

L

am ...........-

.2CE3 ------------

.680 ------------

.Lw ------------

. bn ----––.–.

. m . . ..-.–.-.

.460 -----------

.374 .-–. -.–.-.

!2 Em oyllndera. .. .._. -...__. 0::9.J :&o :2 :g 0.721 0.765 a :g y% asm -----------

~ ... ... -----

d ELk3:&t:o?L ---------------- .194

. na

.289

.7643 .m ----. -...-–

. m .m .727 .780 .&m . no .s32 -----------

Namlle @tion B-l-A, fahedmto wmg I

~ g%.z’k~mz;::::::;::::: 0:;g am CL% 0.623 0.709 0.761 0. 7s-/ a7&

.360 .611

0.b?.o ----------

05

.6%9

Rin 3 pmltlonf&.__ . . . . . . . . .

.7’59

:%

:% ~:l–:::z:

Vfaiibie ring -V--. ____ .. .. ..

.192 :% .513

.193

.aa .723

. 6M

.317

.eS3

.7%)

N. A. 0. A. @wing--. .._ .. _______ .194 .3@

.719 .7E3 .734 .737

.613 .@l .ES7 .m .72S .668

.462

.30J .-.--.-.––

-----------

Nacdle mtion B-l-A, nrdolmd I

M.A. C. A. WWhl&___.__.__L.– 0. W4 o. m 0.641 0.13U3 am o. n3 o. n4 a534 0.!4%9 .--–. ––-.

Nmelle ~,tion A-l-B, Lured Ma uing

[

2 m.Old:%;::::::::::::::: : ~g %!J 0:% :% ‘%

0.749 0:~ 0..$39 0.3s1 .-.. -.––-.

Rmg pmltion 2_ .. ..- .. . ______

. n6 .636 ----------

05 .304

u

. no :%

Vannb e nn –8”. ..__ . ..._.. - .19

.761

.354 .4s7 .657

.722 .601 ------------

N.

.666

C. A. @w rig_ -._.. _._.. _... .MS .349

. .?3.5

. 46a

.703

. @l]

.5!3 .M-5 ----------

.On . n6 . n3 .m .404 .. .. ... . .. ..

NamlIe pmltbn A-1-B, nn@@i

ed oytidm .--.. -... -....-..

z ~~ R A. hind ____________

o. 1s3 llg a ml 0.016 0.700

. 1s6

:%

I

0.767 0.n4

.4s2 .6W .630

a 646 --.-..-.–--

m. Ring 3j position AL--. ..___-._. .180

.733

.Mo .m

. 7WI

.612 .m.s .727

.626 ------------

.746 . n8 .6s9 -.-._.-----

NasaJ.lepxition A->B

.

g ~ ~~nda ----------------- a204 a 391

N. A. 0. k. hOOd___________

0.649 LIE am a= am 0.678

.3?4 .bls

am ---. -.-..-–

m. :% .335

.m .771 .7a

Ring Z @tIon 2.._. _________ .073

.707

.770

.4S3 ----------

:%

.621

Vmbleri~ -W.. . 1s9 .379

.890 .7M .696 -----------

. — -----------

N. A. C. A. mw rig.. ... .. .. .. ... .. ..

.053

. lm .370

.740 .7M

.619

.737

.640 .720

.467 ... ... . .... .

.770 :?% .700 ..%0 ----------

681
682 REWOEL’ NATIONAL ADVISORY COblMITTE 33 FOR AERONAUTICS

TABLE VI.-PROPUL43IVE EFFICIENCY-Continued

J%=v

Frqdler No. 4412-4 feet. &t 1~ at 0.76R. An@e of 8tt@i =+5”

I

v.

nii

m ofnacelle

01 a2 0.8 0.4 0.5 a6 0.7

A’malle pasihon B, side bmmkekramovai

~ a ---------------

N. A. c. 1 bxL----------- :’g %J

Wag % pmtlon 2_--. ..__.-.

Ring 3,~tlon ~-----.–– . 1?6 .347

l#ng 1, @tIon AL._ -... -....-_ ;% .s44

-rir%K%$!?&z::::I:: JIJ, :%

. c. L .wn–ungL___________ .- .192 . .2.$3

0.4!%

.4s3

.4s7

.481

%J

.’504

&’m

.Ei93

.5QJ

.E30

:g

.606

.611

0.646

.C43

.673

.6m

.W

.W

%7

:7Jbj

.715

.7a9

. 7U

. ma

.724

.766

am

.7W

.716

.727

. no

.761

. no

. w

T-4 31-lJQaesa aw .......... .

.lw .’@ ............

-w

.670 .=

.72a

.720 :g

:E

.4!0 1. . . . . . . . . . . . .

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

.m)........–..

) . .. .. ... ... .

. .... .. .. . .

.24;............

h’ecelle pcdtion B, with sidebrmkets

52

I

~@~=-------..---– : g 0.3-50 ag Q* a656 am o.6n cL&5 0: g

N. L C. k hind_________ .350 .euo .676 .7Y6

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

.716

u; Ring & pctsitlon2___________ .187 .351 .4fa .5W .m .725 .748

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

.71M .4m ... .. .. .. . . .

h’adle pdtbn B-1-A, Fdred Into wing

0:pJ 0.646 : ~o a7&

.6% :% .700 .703

.692 .eJM . n4 .718

.s.s9 . al .&m .69s

A’. .L. 0.-4. mwl@______________ am a3s7

Nade ~itIon

0.489

B-I-A.

&w

unfmd

Q66S am 0.673

mo.sm o.* ...... .....

A’iwdle pdtion A-l-B, faked Into wing

NaeelIe @t[on A-l-B, nnfehod

m

Nne?lle @tIon A-2-B

‘i

\

dma -------------- ag UC& a546 a ea 0.749 0:~o 0.840 0.8s3 a 743 . .. ... . ... .

m.rjmd:----.-..-.---– .518

: %%lir%g-rz:::::::::::; ::; %J :: $j %J XJ :g ~g $J ::::::::::::

. . .. .. .

. . c. A. mnVling________ –___ .. .. ... . .. .
NACELIJE COMBINATIONS IN VARIOUS POSITIONS WITH REFERENCE TO lV31TGS

TABLE VI.—PROPULWVE EFFICIENCY-Continued

_ (T–AD) V

‘–~

Pm@kr No. 4412-4 fmL Set 17”at 0.75R. Angled attaok=+lOO

v

~D

Type of nmalle

O.1 02 03 0.4 0.s am 0.7

I

0.8 0.9 LO

Namlle pcuitionB, Me bmcke@ removed

~ I E-crhdm.- . ...-.-. -..---.l o.l&O I Q329 I L1444 I 0.523 I Q675 I Q696 I 0.S76 I 0.490 I Q2Ki l______

tJ N.-A.C.~. hind _.. . ..-- ... . .._. -. 1s1 .334 .467

1

.647 .W3 .K44 .@d -..593 ‘. 346 ..____:

~ %!%%i$’::::’::::

,;g ,% ,% ,% ,@& ,g :%: ,% .324 -----------

: ;%;l:$PSG-:::::::::::::

:K.! % :E :% :%: :g ::: :% :% :::::-::::

.376 -----------

.183 .2M .457 . mu .W!3

O. A. wwlhL_.-: . .. . ----------

.6s6 .641

. 1s3 .340

.6s2

.474 .65s

.426 ..-.– -----

.617 .L127 .640 .690 .m ..-.-------

Necelle pcsitlen B, wltb tide breckets

Erpmed Wllndm -----------------

z N. A. C. A. hind_-._ . .. ..__-

0.181 am a4A6 %64s CL@ aw

. lW .4s

Q 646 cL6a3

.E43

a 450 .-..--.----

m“ FtJng3, pdtlon 2----------------

.611

. 1s4 :R

.202 ---------

.471 .6% :%1 :E . em :E .26s –.--- . ... .

Necolle @tIon B-1-A, faked Into wing

[

a 460

z E=.T;;L-:::;::::::;:::::: a ;Z ?% .&l

a% am3 a5w aw a44s auo

.m .616

. . .. .. .. ..-

.S3s .4m

m“ RltI 3, ~tion 2_-.. -.._.__.. .182 .335

.@O -----------

Va&ble rina -W..... .. . . .. .. .. .. ;% .s33

.457 .644 .595 .612 .W4

.462

.607 . !U7 . ... ... . .. .

N.

.657 .619

0. A. WWML ----------------- .336

.64s .636 .bw

.46s

.244 -----------

. .m7 .57s .690 .W4 .430 -.-.----– .. .... .. .. .

Ne.cnllepmltionB-l-A, tmfehwi

N. A. C. A. mwllng ------------------ a R2 a 340 CL459 a667 a 611 am ama a 461 --------- ----------

Nemlle pmltion A-I-B, feired IntcIwing

!

Eq)osed oylhdm -----------------

S N. k 0. A- hood_ . . ------------

a Ea a 361 a 476 a 671 a627 a6s2

.182

c1647

H

a 617

.2S4 .454 .639 .bw .IY16 .m .6e4

aa .. .. .. .. ...

m“ RI 3 posltlen2 .....-_. ..--- .. ..

.4e41 -----------

Ve%%b}ering -& . .. . ..-_. .._._

.183 .237 .460 .552 .612 .6WI .I154 .626 .644 -----------

. W-5

N. .

.45S –--.. . .. . .

O. A. mW~g-.-.----.-..------.. ---------- ..--:?.. .---:!! !.... ...!-!!.. ..-.:! !---..-: ?----.-:! !.. _-!!!.- . ... . ...- ..-.-------

NocaJloBitIon A-l-B, anfahed

E- oyllndeu -----------------

2 N. A. O. A. hind ____ . .. -------

a 179 am a 463 am : :g a627 a603 0.627

.182 .461 .55-5

1

a342 ... . .. .. . ..

.615

m“ Ring 3, pmltlon 2_.-. _________ .179 :% .462 .539 .M7

.420 ----------

:% . 6?1 :% .520 ... ... . ...-

NomUe pmition A-2-B

683
REPORT NATIONAL ADVISOEY COMMI’JTEE FOR M3RONAUTICS

TABLE VII.-LIJEl7 COEFFICIENT WITH PROPELLER OPERATING

CLP=$

Pro@eT No. 4412+ fek M 1P at 0.76R .&r@ ofattaob-b”

v

‘-rype Ofnacelle

~D

0.1 0.2 ().3 0.4 0.b 0.6 a7 0.8 0.9 1.0

—

NawIle pdffon B, sJdebracketsremove-d

1

~ ~dms-------------- ---------- ---------- ---------- a 187

g N. L O.y. heed___________ ______ . .. .. .. .. ---------

0.174 ala o.1s5

.177’

0.169 ~ :oJ

. Im .157

0:;6J

.162 . 1s0

2 Rti a mkationa-------------- --.-..--– ---------- ---------- . la .170 .lW

~ Ring q WUMIon3___________ .. .. ... ... -..---._- ---------

. 1ss

.216

.161

.177

. Im

.1.57

.160

. lm

Rbw 1,position 2___________ -------- .... .. ... . -------- . 2J0

.151 .162 . 1ss

.149

: :%;ie%””s::-z::::z::: :::::::” ::::::::: :::::::::: :%J :; %J :% :g ;g

.167

.169

0. A. cowlln&___________ -------- ---------- .. .. . .. ..

.100

.132

Nacelle @tion B; with aidebrackets

~ a~d~----------------- -------- .__._.: --------- 0.M3

2 N. A. O. A. head ____________ --------- ---------- -.–.-.-..

a 16$ 0.lm o.M3 : ;g

.107

a WI

.Iou

a 151

G w% PaWon a----------------- ---------- --------- ----------

. 1s4

.173

.167

. 1C8 .102

.100

x .161 .161 . ml

Nadle @tIon B-l-A, fabed into wfng

.1

;-

~ w~m--------------- -------- 0.Im $ N. A. c. A. h~__________ -------- :::::::::: :::::::::: .205

~ ~~~~~~On~-.-_

a 173 0.109 0.100 a 16s U 162

. lW . 1s0

a 163

.172 .159 .106 .155

–8=._.__.__::- ::::::::: :::::::: ::::::::: ‘–---–- .162 ---7ii-- ‘--uifi-- ‘Ti%-- ‘--riii-- ‘---rifi-- ‘-----~iii”

0.A.cowling____________ .-..-—.. .-..--_-- --------- .= .210 .m .leo . 1s4 .179 .174

Nacelle WSItkm B-I-A, anfaked

N. A. C. A. cOWb&!__________ --------- --------- . . . . . . .._ 0.25s am o. Ml a 103 a 165 a 166 a lW

Nacelle ~tion A-l-B, fdred Into wing .

1

~ oY~~––--–------.– --------- ------- ------–– :MJ

2 N. k O. A. hood_________ –.----.– --------- ..-.–.--.

0.142 :;: a lol 0.la ~ ;7J a 177

: !!!!~;g~:~::::::::::

-~:--:: ;:X::: :::::::: :]: ;$ j$ :x :% jg

.104

.167

.107

. . . ---. -.. -. .--— -.— ----- ... .. ... .. —.. -.-. — .170 .140 .133 .127 .127 .131 .139

NamIle pmition A-l-B, nnfe.kd

~ cw~den.––-----. -..–.– ---------- ---------- --------- 0.145

% N. A. O. A hood___________ -------- ------- –--..--– :g

ala 0.173 : ;g & 191 0.197

. la

aau

G - & *~On 2----------------- -------–- ---------- -––---–

. lml . Ilm

.141

. lea

. 14s

.100

.161 . 16s . lea . lR

Naselle PUMOII A-2-B

.1

~ w~----------------- ------– –------– -------- a U8

z N. L O. A hood___________ ------------------- ––-–.-.

: :2J

. U4

1

alm am :g 0.139

.114

~ :$

.117

“ V%%M%Z3Z:::Z::::H: ::::;:::: :::::::: :::::1: ----:@-- ----:%J ;~: JZJ J: Jx

.123

————.. ..-. -. —---- .. .. ... ..- ... ... .. .. .. ... ... .. ..

N. .L O. A. cow ~_________ -----.-.– .... ... .. . -.–.-.-..

.123

.142
NACELLE COMSINAITONS IN VARIOUS POSITIONS WITH REFDRDNCE TO ~GS 685

TABLE VII.-LIFT COEFFICIENT WITH PROPELLER OPERATING-Continuecl

(?Lp=~;

PrqMlarNo. 4412-4 fw~ Sat IT at 0.7SR. Angle of ntteck+’

a

‘f’gpo of nedfe

-“I’’I’’; ’’I’’I’’1 ’’1’”

N8mUe pmitfon B, eidebraoketsremoved

Ill

Em lfndere..-- . . . ..-.-. ----------------- –------– 0.’9J ~~ -m :g flg :%

# N. A, 0.% bowl -------------- --------------------------- :%

a414

‘: E

EUng3 padtion 3---------------- -----------------------------

8 Rfng & ~~()~ ‘_._. ._._..._- . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

.4% .’10 Ag .3$s .3s2

.’51 .&

.377

.W

j g&g~pmltfm2_.. .-. -.-. —.—.. . . . . . . ..- ---. --. ----- .-. -.. — .4M .431 :% .403 X& :E %J’

pceltfon 3_.-. .._-.__.. -------------------------- .’63

Vafiabh rfw-W-_.-- . . ..__. ----------------------------

.425 .WJ .s .2s7

EA. o. A.cowling_-_. _..-. ......... ----------------------------

.476

.451

.2M .m

Nwelle IXHItfonB, with sfde brackefa

., , j:g : : ~: ;. ; :

ExPQ@ tide --------------------------- -------- .. .. .. ...

z N. A. Q.z hc.xI-_._..-... . .. ... .. .. ... --------------------

m“ mg%-titim~-.---.-..-...– ---------- .. ------------------

Necelfe PoMon B-I-A, feh%dinto *g

I

H

Erpawl Undma..___ . ...__- -------- . ------------------

2 ;bLO.~. hd------------------ __.__: ...–.--. ---------

0.47a o.43s 0.us aw am a’fe

.475 .447

a3fra

.’27 .’12 .402 .3M

pmftlon 2___________ ---------- --------- ---------- :% ;% .W :% A# :$

.3W

m“ V&&etig, -&---------------- ---------- .---:...- ----------

.417 .333

N. .0. A. Wwlfng ..... ... .. ... .. .. .... ---------- --------- --------- .4M .= .424

.3E0

.416 .’10 .4a3 .’04

Necalfe@tionB-FA, nnfehwf

~1’4”laml’4’’lamla”’!aml am

N. A. O. A.cewlfU--._..– . ..-_. ----- --...---–- ------- . ... .. .. .

NawRe pmltfon A-l~B, fefred Into wins

H ‘% ~ ~ ‘E ‘g ‘% a=

E- Undas .._. __.__ . --------- ---------- --------- LIWJ a397 :% ~~ y% ~g 2 NtiA. 0.% hood.___________ ----------------------------

pdtin~---------------- ------------------- ----------

d VarMe ring, –~.-.-.- .... .. .- .. -------------- .. .. .. ... .

N, A. O. A. wwti -------------------- .-------– -------------------- .39.5

Nawlfe IU@Aon A-l-B, unfefmd

i 1

I?spcuod Ilndera. . ------------- --------- --------- .. .. ...._ a3a fLg a 401 a407

z N.~0.~.h~---------_----- .. .. ... ..- _.__..: .. .. .. .. . :% -w :g ;% :% :g

c1u“ 0.‘U a410

m ~%~tion~...-------...-. .. .. .. .... ---------- .. .. .. ..-

.4U2

.3%3

Nacelle PMMen A-2-B

1

!11

E- Wdm.- ....---. -–--... -.- .. ..-! ------------------- a3m a353 ak a300 a333 :g I

ti N. AO. ~h&-------------------------- -------------------- ;~, ;% :% :Z5J :% -m

.376

lung pmitfonz --------------- ------------------- ----------

.%3s

m. Verfabe7 tig ---------------------------- --------- . --------- .340 :g $.EJ .3s3 .3s9 .3W

N.

:%!

O.AWWU— --------------- --------- ---------- ---------- .354 .W .3s1 .333 .2$4

,

.
.. —. ——. ..— -u .-—

686 RDPORT NATIONAJ ADVISORY COMMTITEE FOR A13RONAUTICS

TABLE VII.-LD?’T COEFFICIENT WITH PROPELLER OPERATING-Continuecl

Pre@fm No. 442-4 fe& Sot IT at 0.76R. Angle of attaak-+d”

v

nii

‘1’ypa0[made

al a~ a3

I

0.4

I

0.5 0.6

I

&7 0.8

I

a9 1.0

Namlle pceition B, dde Inneb& renmved

.I

“ Espassd oyIfndera_________ --------- –––.-.- ---------- 11~ CL69S abm aw4 cl% a636

1

N. A O. A. hood___________ --------- --------- .-.-. -—- .m

a e31

U % &tIon 3---------------- ––.-–.- --------- ----------

.670 .M1

.762

.ma .633

.ma .6E3 .646 .531 Ring%wsttton 3----------- ------- -------- ---------- ; p8 Ag .660 Ag .628

.624 .&u

.619 .613

j Ring L I@tten 2--–----––––––––– ––––– ----––– --------- :% ;% :M ;% .m :~ %J

.670

~ %%Jeti% -P

tfon 3_________ -—–– -------- –––.-.- :%

-----.-.-.-——— .-. .-. —— .. ——-. — ———----

0. A. cnwlfng___________ -------- .-.. -.-.– ––––- .73s .703 .539 .672 .Wo .646 .m

NemIle position B, wfth side braetets

I

~ 0~---––--------– --–--–– --------- -------- : ;g a% :% y% := clg :% z N. A. O. A. heed________– ------- ----------–––--.-

~ Ring & @tfen l______–___ -------- --.-.---.-––––– .Z77 .6s9 .667 .652 .640 .631 .627

Ntwalle @tfon E-1-Aj H fnta wfng

‘1

Em lfnders__________ .-.-.-.-– -------- --------

@ N. A. O.~ hind_ . . _________ ------------------- ----------

a 758 a 7c8 a670 a 646 ae30 :$: a 610

. 7aI

m V%h%ti>?::::::::::::::: ::::::::::::1:::: ::::::::: :: ;g %J ;: ;g %J :g

N. A. O. A. wwl@____– _______ --------– -—----- ..–.-.-..

N- peMen B-1-.4j unfdred

N. k O. A. mw~------.-–--.—–.-.-–– –.-.-.-.-.-.-–—- a76s a7a3 am a637 aom aw a ml

Namlb pmkien A-l-B, fafred into wing

1’

~ Omti ------------------------------- .. .. .. .. .. a665 a653 aw a639 :% a6z3 a6z3

s N. A. O. L hood_ ---. __.. -... --._ . .. ..__. - -------- .lEa :% .6ss ;:

~

v~~emtitionk ------------------------------- ---------- :% -w := m :% :& .:%

–P---------- .––----------–– ---------

1

N. A. O. A cinvW ___________ _____ ----_---- ---------- .667 .551 .63J

. 6!UI

.631 .626 . ml ,ul

NacaUe pasitlon A-l-B, unffdrd

z

Expwd 0Y~dfX6._–---–––_ --------- ––––– –––—- 0.691 am :% clg am amd

N. k O. A. heed-_____—–_ ----––– -------- -------- .553 .R59

aa

m“

.es$

Ring & pudtin 2_________ ----––– ––––-- --------

.m

.fiis .W .$51 .646 :% .634 .6?9

NaceUe p-millomA-%B

I

~ **---------------- -------- -–-—–- –-–-–- aea ag : 61g (lg 0616 : 61; ~:.

.61.5 z

N. A. O. A. hind-----––.–––––––– –-:::;::

::::::::: --------

“

Mll##?Ml$L ---------- ---

--.-.-.-

:E .613 . 61s .621 .631 .1311

.621

.620

--. ——--—----— —-------- .. .. .. .. .. . .. .. .. .. .6?0 .eal :~ .619 .618

N. A. O. A. cowz--–---–––––––– ––.-–.. .-..–.-.- . .. .. .. .. .618

.617

.616 .614 .614 .614 .614
NACELLE COh1131NATIONS UfVARIOUS POSITIONS~ REFERENCE TO ~GS

TABLE VII.-LllT COEFFICIENT TVITH PROPELLER OPERATING-Continued

C“=g

Propeller No. 4412-4 feat. Set 1? et 0.76IL Angle of attack=+l~

I v

1’ ni

— .r .,. -11. .Jp.l —..

0.1 a2 0.s 0.4 Clb 116

I

0.7 L8 ao Lo

NamUe pmitlon B, side brackets ramovw.1

s IEXIKHJXIeyllnde)ra----------------- . . . . . . . . . . . . . . . . . . . . -.---.----

j N. A. O. A. hind. ___________ ---------- ---------- ----------

1

IUng 3, pmltlon L----------------- ---------- .. ... . ... . .. .. ... ..-

~ Ring 3, position 3_ . .. ... .. .. .. .. . ... .. .. .. ----.-.-.- ----------

1 I#ng~pmltlonL . .. ... .. .. .. .. .. .. .. .. ... ...-. ----------

~ V%leriOE- 80 . . . .._. _...-.. ... ... .. . -....- ---------

, pmition 3-.. ____. ... . . .--------- ---------- ----------

. . 0. A. @\vbg -------------------- ---------- ---------- ----------

L@

L 075

1.or I

L02

1.m

L03

i~

I

(

——

I.Wl aw

.m

.678 :E

; .9745

% .978 :E

K1 .m .m

a .~ .921 .W3 .952 I

a 912 am

.912 .m

.918 .m

.912 .W4

.918 .m

.s07 .m

.S&3 .m

.QM .916

a 874 a w

.W .WI

.?s7 .87a

.8s2 .67a

.m .&m

:?& .670

.wl

.W .m

Nacelle position B, with side braekek

Er@mMI landers.._ . .. _______ ---------- ---------- ... .. .. .. .

2 N.& O.~ hind _._.. . .. ... .. .---...--- ---------- ---------- :: E

& Ring a, @tIon 2.— .. .. ... .. .. ... .. .. .. .. .. .. .. .. ...- ---------- LOZO

, a% ‘g~ ‘Z ‘8 ag

NamUe PmMen B-l-A, faked fnto fig

Tb*a*g-*”_...~.~ :% :% %! a! ;g j a~

Em lindara._ . .. ..._.. ._._. .._._ -------------------- LOZ2 aw4

ti N. A. 0.% heed --.- . .. ... ... ..- . .. .. .. .. ------------ ---------- L C-t5

Rln a posttionZ.--. ... .. .. . . ... .. .. .. .. .. ... .. ----------

N. A. O. A. row@ -------------------- .... .. .. .. .. .. .. .. .. .. ... .. .. . 1:a32 .890 .9M .036

Namlle pmitfon E-1-A, nnfalred

N. A. O. A. mwUW_---.--_---...-... ... . . ... . . ... .. .. .. .. .. . .. ..- 1.040 a963 asms a w am am a 811

Namlle @tIon A-l-B, hired into winc

J I ~~ ,% q~ a~ a$J

Exrmsed IJndom----------------- ------------------------------ a 971 a940

Z N. A. O.%. hd---------------------------- ... .. .. .. .. .. ... .. . .936

EbI a @tlOn l-----------------------------------------------

Va%b\e ring –W-------------------------- ... .. ... .. .. .. .. .. ..

O. A. mwbG .. ... .. ... ... .. .. . .. .. ... . .. ... .. .. .. . .. . .. ....-

Nacelle PosMon A-l-B, unfalmd I

ErPti oyllndera. . . .. .. ... ... .. .. ... . ... . .. .. ... ..- ----------

2 N. A. O. A. bad. ___________ ---------- ---------- --––--–

~~ atu6 a 919 awn afw atao o.m

d

.940 .916

Ring 3, pmltlon 2--.. . ... . .. .... .. ---------- ---------- ---------- two .9M

.S37 .s5 .877 .s70

.916 .m .m .= .m

Nacelle titlon A-2-B

687

E-d lindara._ . .. .. ... .. ... .. .. .. ... . ---------- ----------

% N. A. O.~ hind -.- .. ...__ .. . . ...----– ---------- ----------

a 9r2 afaa o.SsI a 675 afm a8r2

.919 .936

asm

.E%6 := .m .876

Rfn a ~flon ~... - .. ..-- ....-. ---------- ---------- . .. .. .. ...

.6?2

ti .831 .m :=

Va%ib~e ring –8’’ __________ ---------- ... .. .. .. . ---------- .’am :%

.s77 .m .88s

N. A .0. A. mwtie---------.-.--.... .. .. .. ... . ---------- ---------- .877

.s78 .672 ;% .289

.S71 .8s3 .S6a .m
6S8 REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

TABLE VIII

MONfiNT COEFFICIENT WITH PROPELLER OPERATING

RoBIIer No. 4412-4 fe%L Set 17 at 0.76R. Angle of attack- -5°

v

‘nD

Type of nacelle

0.1

I

o.210.3!a410.6 0.6 0.7 0.8 0.9 1.0

—

NamIle psltion B, dde brmkebremored

h’.

E- cylinders -------------- ---------- ----.-.-– --------- -0.113

N.& O. A- bmd________–__ -------- –––...- --------- –. 116

R@& @tlon 2____________ .... .. .. .. ---------- ---------- –. 111

Rtng 3, posltlon 3---------------- --------- ---------- ...-.–.-. –. 113

IJblg 1,pMIHOn2_- . . ....-..__ -------.-- ---------- ---------- : ;;:

v%M%%%:-----------

--------- ------- ------ _,m

.—-. —-. -. —.-. —-------- -- —------ .—--—---

.0. A. lx@fng--_..___._._– ------- ---------- ..-... –-. –. m

<Q&

–. m

–.Oz3

–. 033

–. C@

–. m

–.@z

-a C&9

–. m

–.m

–.ma

–.m

–.IsN

–. m

–.a37

-o. w

-.w

–.w

–.C&f

–. m

–.ass

–.C@3

–. m

1

Nadle @tion B, wftb dde brackets

——

-_: g

–. w

-.as2

-. cm

-. Cel

-. m

-. am

–a 076

-.079

-.079

–. 079

–.m

-.078

–. 076

–. on

-_: &o

-.on

–.017

-.070

-.076

-,076

–. 076

ders__-–._._..- –--.----- ---------- .. .. .. .. .. -0.101 –o. all -am -_a g –o. 077 -_a &6 -0.074.

–. 113 –. 037 –. m -. m

g

m.l%d_ .. ..__ -------- —-----—. -- .-—---- ---------- –. 077

m. Ru ~, &* ~----------. .. .. .. .. --------- --------- –. 107 –. Q33 –. w -. @5 –. ml –. 079 -.077

Nwalle @tiom B-l-A, faked Me b

~ Eqmssd @Inden. ...-_. ._._._ --------- --------- --------- -aa –0. m –a m -a 074 -_: g -o. M4 -0. oxl

N. A. O. X. hmd__._.__-_--– ---------- --------- ----------

* v~~g”~$--------_--””_ .._

–. 102 –. U?8 –. 076 –. m –. w

.- .-. . .—------- ---------- .. .. .. ... . -. ----—-- ---------- .... . ... .. .. .. .. ...- .... ... . .. ... .. .. .. . .

-- — ----------- -.—-.---- -—------- .. .. .. .. .. –. 131 –. Km –. w –. m –. MM -.091

N. A. O. A. mwti--.-.------------- --------– --------- ----------

-. m

–. Iw –. 112 –. m –. 07s –. 070 –. m -. m

NacaUe positionB-I-A, unfdmd

N. A. O. A. cowing ------------------ ---------- ----–----l-- .. .. ..– –~ ~ ~QJ7 –L a30 –a am -o. w -a 0s9 -0. 0S5

N& pasltfon A-l-B, hh’ed Into wing

1

gErPc@d Wtiam ----------------- ---------- -------- --------- -m& –a m –0. m --- ~ –0. m -0. m –cl 070

N. A. O. A. had---------------- . . . . . . . . . . --..------ ---------- –. 073 –. am –.cm –.w

e :%k%ti~r?:::::::::::::: :::::::::: :::::::::: :::::::::: :%J :5 ;%J ;g yJ’ :; ;~

-.m

N.- .0. A-wbg-.--–----------.--- . . . . . . . . . . . . . . . . . . . . ----------

N’* rdtion A-1-B, nnkdmd

z

Em @nder6__________ . . ... ...- .. .. .. .. .. ---------- –0. W-4 -a w –_: ~ -a 072 –a 074 –a 074 -0.074

N. A. 0. A. hti---------------- ---.------ ---------- ---------- –. m –. m –. 077

m“

–. m -. m -. m

Ring 3, positien ~.--–.--_–- --------- –.-..-.-. --------- –. cm –. 075 –. Oi’o –. m –. @-s –. w –. m

NemEe - A-2-B

I

gEmlsed wumlOm---------------- --------– --------- ---------- –a m –: ~ –:g -o.m -0. m -0.07’6 -a 073

N. A. C. A, hood ___________ --------- . . . . . . . ..- -------–-

; :&\~~y$-”’--””-”_”_””””

–.U20 -.070 -.077 –.am -.ml

. . -------- ---------- . . . . . . . . . .-.. -.-. — --------- ---- —---- . . . . . . . . . . ---------- ---------- ------------

-- —. . ----------- ---------- —-------- . . . . . . . . . . –. cm –.Wo –.m –.on –.079 -. an -.C@.s

. .c’.A. -W------------------- ---------- --------- --.--.-.– –. on –.0$!? –. w –.m –.074 -.077 -. am

.-
.

NACELLE COMJ31NATIONS ~VARIOUS POSITIONS ~REFlIRlIN C13 TO lVll?C4S

TABLE VIII-Contimmd

MOMENT COEFFICIENT WITH PROPELLER OPERATING-Continued

PrO@lOr No.44124 ki Eat1P at 0.76l?. An@e Of at@ok=Y’

m ofnfmne z%

0.1 0.2 0.8 0.4 0.6 0.6 0.7 0.8 0.9 LO

Necalle POSIttenB, dde bracketsmxnoti

I

~ ~% O Ilndms

, ~ Horxl:::-------------

---------- ---------- ---------- ~g :% .-g: _:g -~~ _&~ ~w

~ Rlng”3, pdtion L_..~~~~~~~~~:~~~::::::::: ::::::::: :::::::::: –. Ml ~. –. 073 –. m :% :%

–. w

~ R1433, &tIon 3--------------- ~----.-.. . . . . . . . . . . . . . . . . . ..- –. cm –. 074 –. cm

–. cm

Rfng 1,pmition Z____ ...>..-> ---------- .. ... .. ... .... .. .. .. –. m

–. 037

–. Uxl –. 073

–. Mu

–. 070

–. m

–. a13

position3-------------- . . . . . . . . . . . . . . . . . . . . ...------- :.

–. w –. w

f ?%%&e

~ A ~o%~:---------------

.._-

-. m –. 074 –. 07u

–. cm

-. w

–. on

–. 004

–. 037

–. m

-- ---------- . . . . . . . . . . –. m –. cm –. cm

. . . . . . . . . . . . . . . . . . . . ---------- . . . . . . . . . . . . . . . . . . . . –. w –. m -.072 –. w –. w –. m –. W3

Needle @tion B, with dde braokets

~ ~ und~----------------- ---------- --------- ---------

N.& O.~. Hind. -_ ... .. .. .... ------ ____.: ____.: ::; ;~ -:- %% -% 2E :%

m Ring 3, @tIon 2-------------- . . . . . . . ..- . . . . . . . ..- . . . . . . . ..- -. m –. w –. W

Necelle @tin E-1-L feked into wing

1

~ &%%z%o&----

----------1---------- ---------l---------l-:’; “ ‘:= ‘:: ‘:= ‘E ‘~~

din--------------------------- --------- ---------

G Rh 3 ~tion AL------ . . . . . . . . . . . . . . . . . . . --------- ---.-.----

Var%b\e rin #---------------- ---------- --------- . . . . . . . . .

N. c. A. mw&----------------- . . . . . . . . . . . . . . . . . . . . . . . . . . . . m% :% -.W -.ols -.M -.lm

Xac3Jk *den B-l-& unfahzd

N. A. O. A. Cowing ------------------ .. ... ... . .. .. ... ... ... ... .. .. -cl ml -lla30 -a M-7 405s -am -a W9 -0.040

Namlle @tIon A-l-B, faked into wtng

y,,,, ~ ,,,,,,,,:~::--:: ‘:! :XJ -.. ;~ .-;%J

ders--_ .. ....__... --.--..--- --------- ---------- -am -o.lxa -am -0.070 ~g -o. m

;%:h~y~?k:::::::::::- ..----- ----------

N. A. O. A. COW no------------- .. .. .. .. .. .. .. .. .... .. .. .. .. ..

NamUe pMAon A-l-B, unfelmd

z

1 I % ‘E ‘:E ‘:% ‘: ‘~ ~~

E- llndas _________ . . .. .. .. .. .. .. .. .... ... . .... .. -aW -o. m

N. A. 0.’%. Heed ___________ --------- .. ... . .... .. .. .... ..

m“ Ring 3, pmttion z_._ -_.-. _.. ---------- . ... .. .. . .. .. .... ..

Arwelle pmition A-2-B

Ill

Eq.xe.ed linden __.. _.... ___ --------- -------------------- –0.023

5 N. A. O.~ Had.. __________ _.. ___-:____ ----------

-. g +0s4 -am

–. 021

–o. 070 –o. 075

–. m

-am

–. ma

–. 017

–. MS

–. 040

–. 072

–. CtM

–. 075

;.

~t?$titi$~<:::;::;::;::::::: ::::::::: ::::::::::::::::::. 2% ;- :% ZE :$ 5: :%

.-.-—---- --------- ---------- --------- . –. m –. 070 –. 075
RDPORT NATIONAL ADVISORY CO ~E FOR MilRONAUTTCS

TABLE V1l-Continued

MOMENT COEFFICIENT WITH PROPELLER OPE~TING-Continued

c

Mp

“p=&

Prapalfer No. 4412-4 feet. Set 17”at II 75E Angle of 8ttaok-+5”

!

v

Type of aecaile

~D

0.1 0.2 0.3 0.4 0.b 0.6 0.7 0.8 0,9 LO

NacaUapasltfan B, efde breoketsremoved

~ $~ 3

-M O Udders----------------- ------------------------------ +092 ~~

N. A. O. K ti~------------------------------------ .. -------- –. 100

Rfng 3, @tIon 2----------------------------------------------- –. W2

Rfng 3, pmition 3– . . .._ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . .

Ring 1,fxmltfon2_-. _.-_. .._._ ------------------------------

Mu 1 @ti8-----------------------------------------------

Va#ib~erln -&-----------------------------------------------

O. A.mw g--------------------------------------------------

~: g

–. 0s3

–. M3

–. m

–. 369

–. 032

–. M2

-0.062

–. 05a

–. 068

–. 067

–. WI

–. m

–. an

–. 030

-a059

–. 058

–. o&5

–. 0.55

–. 058

–. w

–. 055

–. as7 T

-0.067 –o. a53

–. 064 –. lx-f

–. 064 –. a52

–. 061 –. m

–. m ~.

–. m

–. m –. 052

–. 055 –. 066

I

Nacnllepcdtbn B, wfth side brackets I

~ cw~dfw--------------- ---------- ---------- ---------- -claw ~:% ~k& +fJ -a 054 2 N. A. O. A. h@xf_..._.._.__.- .. .. ... ..- ---------- ---------- –. m

6 Ring 3, pmflian 2__-. --_ . . . . .._ ---------- ..-.----.- . . . . . . . ..- –. w –. 669 –. oeo

–. m

–. 057 –. 063

Namlle pc=sitianB-1-A, fahed fnta wfng

1

~o ~d~----------------- ---------- ---------- --------- -a 118 –-~ –a 070 -o. W -aO.u

ti N.& O.~. hmL---------------- -.-.------ ... ------- .. ... . ... . –. 109 –. W-5

R 3 pmltlon2- .. .. ..__. ___ -.------.- ... .. ....- ----------

-.0.56

–. 100 –. 078

–. 049

–. 062 -.062 –. O-f6

–. 115

:. TJ?:k%::--:___

--------------- ---------- ---------- ---------- –. 0s4 –. w

–. G-R

–. w

–. 077

–. 047

--------- -------- .. _------.- .. -------- –. m –. Oxl –. 043

A’amdlepasftion R-I-A, nnfafmd

TI -o. aw -a049

–. 046 -. on

–. Oio -. m

-.046 -.046

–. m –. 036

N. A. C. LmTbL ------------------ . ..-------- . ... ... ..- .. .. ... . .. -0. ml -0.076 -o. w -0.067 -0.6M -0.047 40!5

I

h“acellepodtion A-1-B, fahed into wfng I

.1

~

hdm ---------------- ---------- ---------- ---------- +067 -y& ~@$J –m&l -0.073 -Q IJ7b

~ N. AO.%M-;---------------- . . -------- ---------- ---------- –. Om

–U 076

padtien 2_ . . . . .._-._ ._. ---------- ----.-.-– ----–---. –. 07’0

–. 076 –. 076 –. 076

: :%be~-e -----------------

. . . . . . . . -..-.. ---------- :g :. :- :$; :-; :~ :#

–. 073 –. 076 –. 075 –. 076

.O. A. Caw g-------------------- .- . . ..–-. ---------- -.-.----.-

Na@le pwkfan A-l-B, nnfafrW

Ifndere . . . . . . . . . . . . . . . . .-------.- ---------- 2 Rm. T.w-:---------------- ---------- --------- :::::::::: ~% Zg% ;g -’!:E -. g :E

–_: ~

oi Ring 3, @tfon 2- . . . . ..-. _____ . . . . . . . . . . ---------- ---------- –. W4 –. ml –. 076 –. 076 -.076 –. 076

Naa3napdttarl A-2-73

“1o landers..__. ._ . .. .._ ---------- ... .. .. . -

~ ~w.~.hd..------..--...-.. -.------.- _......:. :::::::::: *.F7 %! 2EH

pdtien 2------------- . --------- ---------- ---------- –. @)o

* ;%~ew–p---......-.-.---- ---------- ---.----.- . . . . . . . ..-

–. 037 –. 066

N.

–. (04 –. 040 –. 057

0. A. mug—. . . . . . . . . . . . . . . . . . ---------- . . . . . . . ..- ---------- –. 012 –. 042 –. 067

-awl

–. 0a2

–.C&

–. (w

–. mm

-am -0.074 –Q 076

–. w –. 07u -.072

–. 667 :$ –. 073

–. 098 –. 073

–. w –. m –. 069
NACIXJ.ill COMBINATIONS IN VARIOUS POSITIONS WITH REFEFWNCE TO WINGS

TABLE VIII-Continued

MOMENT COEFFICIENT WITH PROPELLER OPERATING-Continued

Pro@ler No. 442-4 fa&. @t 1P at 0.75 R. Angle of athck=+lp

v

~D

Typa of namlfe

al a!2 0.8 a4 0.6 fL6 0.7 CL8 0.9 LO

Nacelfe pceltlon B. side breekeia removed

a

1

Exjxued llndere. ...-.. .__.-.. ---------- --------- --------- $WJ ~g –: g -o. Mo –o. owf +054

N. A. O.~. hewf--------------- ---------- ---------- ---------

–0. 0-58

I@ 3, pmftion ~-------------- --------- .-------– ---------

–. a57

-.036

–. 065

–. m

–. 054

–. am

–. 054

–. w –. 060 –. m

Ring & PLwItfon8_._. ._._. ___ -------- –. mu

–. O&I

j R# ;, PC&l: ~:::: ....__-.. ____.: ::::::: :::::::::: ~. 2.E ::@ ;% :%J :%

-. ob9

–. 0ss

UJ ------------ .-. .. —-. .-.-.--.-— .. -.---—

Var!3bie rfng –W:--------------- .. ... ... .. --------- ---------

–. U37

–. Ml –. w

–. m

–. 057 –. w

–. &u

–. OMl

N. A. O. & w~------------------- ---------- --------- -----—– –. 074 –. w –. M9

–. m –. O-10

–. M-5 -. m –. Osl –. Om

Nacelle pasftlon B, wfth afdobrwke~

2

Ii

ExposMIo Undara.__._.-__. ------- .---- —--- .. .. .. .. ..

N. A. O. ~. hind----------------- -------------------- ---------

~; g ~: g –_a ~ -0.067 -flw –: ~ -o. W

05 Eung8, pJ9ftionL..-; ------

–. 0s4 –. 05a

–. 073 –. OeJl -. m

–. m

--------- -—------- ---------- –. 050 –. 043 –. 047 –. M

Na@Ile pmltfon B-l-A, Mod fnta wfng

11

lfndere . . .... . ... .... ------------------- --------- –0. 108

ti ~=.~. hti__________ _____________ ----------

–_: g –_a g –_Rg -o. OLs

–. 118

–_a &s –a 0/8

>-~

6 Rln 8 pmftfon ~--------------- .--. -..-.. -.----;-.. ---------

–. 042

N. A~O~?~?~g?:~::::::::::~:. ::::~:: ::::::::: :::::::1 52 SE :: SH x x SE

Nacdle pmkfon B-1-Aj nnfafrd

i

N. A. O. A. mtiti ------------------ . . ------- ---------- ---------- –O. a= –0.073 –am -afwo –o. 05s -aOim –R 052

Nadle Pcdon A-l-B, fefrwl fnti wfng

ti

I

1 I

~?A?.~??$:::::~::::::::~ ::::::7-:::::::::: :::::::-” -:g --% --% --% --% --% -:%1

~ %3 POsftbll--------.-.--...-: ------------------- --------- _.on :% :. :. :. ~g :.

v tie ring -&Q--. .-.. -._... -..--.-..–- --------- --------

N. , 0. A. uMfrw____...__. _–-. .. ... ...- ---------- --------- –. W –. 071 –. 074 -.075 -.075 -.076 –. 076

NaceUe @tion A-1-B, nnfefrd

2

/ i

E%.T?*::::::::::::::: :::::::::: :::::::1: :::::::::. ::% -:-. -:~ ---lj -:- ---~ -:--

ni Rfng & pmltion 2-....---.-––– --------- ---------- . --------

Namlle prdtion A->B

ti

1

II

E- Ifndere--._.-.--.––.–– ------ -—------ -------–- -o. oa

‘E~ ‘g ‘% ‘g ‘E

N. A. O.~.hmd _________ ----------------- ...------ ~.fi ---% -’-% -2% -:E -:Z -:E

: V?’h’g?e?:::-:::::::- ::::1:::1::::::

0. A. cow c---------------------- ---------- ---------

::::::::: ~.

691
REPORT NATIONAL ADVISORY CO ~ FOR AJ3RONAlJTTCS

TABLE IX

RELATIVE lMERITS OF VARIOUS COWLINGS FOR DIFFERE NT NACELLE LOCATIONS

HIGH AND ORUISINQ SPEED CONDITION

*W No. 44H feat- Set 17 at M6 R. #~-O.@5 CrO.4Q3

LNacellel~tion.. ----- .__- —_.------- BI B B-l-A 2 B-1-A A-1-B i A-l-B A-2-B

PrOpnldve eRioienoy (v)

1

: m.x~i-::L:::l::::- :~ am am ------------ a 7dI

.707

a 766 y S7;

~ Riuga PraItion 2________~

.764 .-.–-..-.– .730

.EO1 -.– .. ... . ..

~

.%

Ring 3, prsklon 8___________

.743

.TJ4 .__Y!_ .–..—-. ----------- ------------ ------------ _....: ?..

Ring 1,pdtfon 2__________ .845 .-.--------- _________ ----------- .. . .. .. .. .. ....-.-.---- ----------

:. ?%:btiz:$:::::::::~::: ml - -m am

.84s ---------- ---------- ----------- ------------ .. .... . ... .. .-.-..:%..

.7s9 –--––.-– .7F3 -----------

0.& cowling_____________

.m ------------

.719 ------------ .770

Nacelle drag ticienoy factor (N: D. F.)

!

i m.x%&-:::::::::::::: :E ?%

a235s --.--------- aw-2.3 am awu

a -3 Wtfon 2_______

. lm ---------

:1740 .1070

.MOs

.1970 ------------ :E :%

Rfmg & poskhn 3___________

.B16

.1725 ------------ . ---------- ----------- . .. .. .. ... . .----------- ------------

~ %lpmltlen~

1,*fin 2---------------- .2316 –..------– .... .. .. .. .. ------------ ._.-. ----- ...---.----- .. .. .. .. ...-

: T’~bhRti--::::::::~:::: . lmo ------------ J# .. ..K=i.. :% ------------

.3WJS ---------- ------------ ----------- ------------ .. .. .. .. .. .. .. .. ..=k..

. . c. A. mug------------------- .m ------------ .. ... . ... .. . . 10I2

Net ellkfeney (TN. D. F)

1

3 RY%’%!!%l-:::::::::::: %3 ?% au ----------- a46a llg f 4747

~ Rfrrg3,pasltion2. ._ . . _______ .m

.038 -----------. .631

R@8,@tin3–_-–__.-.–_--

.eo7 .. .. .. .. ..-

.623 ___”_l?K ------------ .. .. .. ...._ _._l:!!.- ___:?.. .-. J!!..

$ Y&b~s$!;:::::::::::::

.684 .-–-.------ ---------- ------------ .. .. .. .. .._ ---------- .. .. . .... . ..

.640 ...–.––-- ------------ ----------- .. .. .. .. ...- . ----------- --..--:tii..

N.

.W7 –___.-.-

C.A.~lhg -------------------

.Oas .. ...i.G-- .4W –.- .. .. .. ..

.762 ..--–.-–.. .e80 .640 . .. .. .. .. . . .eOa

lSfdebmoketa mmovti. 2Fafrwf fnto W@

TABLE X

RELAT~ MERITS OF VARIOUS COWLINGS FOR DIFFERENT NAOELLE LOCATIONS

O~RiGOONDITION

PropdkNO.4Q4feA SatlPatO.75R. ~$-O.42. CL-O.@.%2

Nm?lfelecatkm_.. ———---- Bl B B-I-A . B-l-A A-I-B $ A-1-B A-SD

I

Preprdsfveeflkfenoy(tr) I

ISIS%W%%--------------1 a% :% -~ --.-.:-. .~ ?% :El afm ----- --.... am

.024 ..!S3 .__..._z .627 .W .W

[

... & “. *. lIw--. -._. --—-----

/

Rfng 3, pmftion 2_________

Rfng ~ pmftfon 3_–– _____

Rfng 1,$@M3n 2__________

Rfmg 1,pJsftiOn3_______

var. rfng –e

o. A. WTUIIG::::::::::::: I

. W*

..539

. OIS

.64J

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

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

.—-- .UY.l . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

..- .6W .-.-. —-----

11 .023 -----------

,E&,--- -.. ,

am

.m ............

II .61S . . . . . . . . . . . . :ti? I

N.

N. L u. A. nOOa_________ –. W65

Rfng 3, pmltfen 2______ –__ –. ox

–.~ I –-~ Cr2zl .0106

Rfng 3, mtfim 3_________ –. 0m7 ._::!? -------------------- -- .__._J ------------

BE

Rfng L Pr@Men 2-–––-––————

w L mtfm 3–—_——–––

/

. Olcd .-.-.–----- --------------------- ---------- ... .. . ... ..- –.- .. .. ...-

Var. rfng –@___________

–. 0J41 ----------- --------- ----------- __.:G-- ;::: ------ .. . .. ... .. .

. c. L c9uuug __________

–. m ---------- –.W .-.–a.e-- .rM6

–. 0301 ..-. ------– –. o127

.- -----

–. ml .. .. .. .. .. .. .12311

I

Netarlidamy (v–N. D. F.) I

l~l@:q~d~==.--.--l.__.l aw]— awl aw ------- \aml awl awl ..

““o ..-–---––

o ---------

? l------------l-------- ---------- .–-:!-..-l-.-.-. -.-..1.-..........1

LV. A. u. A.n(H3cL __________

R@ 3, *tfen 2_________

Rfnc 8, titfon 3_______

;g] :%[ :a

Rtng 1,FUSItimr2_______ .m -.

Ring 1, *lion a_________ .054 -

v8r. ring –&___________ .078 ..

- c. A. cnwMng_______–__ .071 -.

-—.—————------- ---------- ---------- .-r-._...

-——--_--------------------------- .........-

-—.—-.--- .fm --------- . ........

----------- .634 am :% -.-.-----

-. ....-. .-—..

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

.612

-- .616

1 Side bracken removed. ~Fafrad fnto Wfng.