Wind-tunnel investigation of effects of a pusher propeller on lift, profile drag, pressure distribution, and boundary-la...

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Material Information

Title:
Wind-tunnel investigation of effects of a pusher propeller on lift, profile drag, pressure distribution, and boundary-layer transition of a flapped wing
Alternate Title:
NACA wartime reports
Physical Description:
8, 19 p. : ill. ; 28 cm.
Language:
English
Creator:
Sandahl, Carl A
Langley Aeronautical Laboratory
United States -- National Advisory Committee for Aeronautics
Publisher:
Langley Memorial Aeronautical Laboratory
Place of Publication:
Langley Field, VA
Publication Date:

Subjects

Subjects / Keywords:
Propellers, Aerial   ( lcsh )
Aerodynamics -- Research   ( lcsh )
Genre:
federal government publication   ( marcgt )
bibliography   ( marcgt )
technical report   ( marcgt )
non-fiction   ( marcgt )

Notes

Summary:
Summary: Some of the effects of pusher-propeller operation on the aerodynamic characteristics of a flapped wing were measured in the Langley propeller-research tunnel. The effects of propeller operation on the lift and profile drag of the wing, on pressure distribution, and on the position of boundary-layer transition were obtained. The results indicated that, at fixed angles of attack and with flaps deflected, the wing lift increased appreciably with increasing thrust coefficient. With flaps retracted, no appreciable increase in lift with increases in thrust coefficient was measured. Chordwise pressure distributions at several spanwise stations indicated that the effect of propeller operation was greatest in the region immediately ahead of the propeller and that the effect extended out-board from the propeller axis for about 2.5 propeller radii. Measurements of boundary-layer velocity on the forward part of the upper surface of the wing showed no appreciable shift of transition in the range of thrust coefficients investigated.
Statement of Responsibility:
Carl A. Sandahl.
General Note:
"Report no. L-148."
General Note:
"Originally issued April 1945 as Advance Confidential Report L5C08."
General Note:
"Report date April 1945."
General Note:
"NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were previously held under a security status but are now unclassified. Some of these reports were not technically edited. All have been reproduced without change in order to expedite general distribution."

Record Information

Source Institution:
University of Florida
Rights Management:
All applicable rights reserved by the source institution and holding location.
Resource Identifier:
aleph - 003613201
oclc - 71205044
System ID:
AA00009382:00001


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Full Text

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IONAL ADVISORY COMMITTEE FOR AERONAUTICS


LRTIMIE REPORT


ORIGINALLY ISSUED


April 1945 as
Advance Confidential Report L5CO8


VIHD-TOMEL INTESTIGATIONI O EFFECTS OF A PUSHER

PROPELlER ON LIFT, PROFILE DRAG, PRSREM

DISTREUTIDN, AND BOUNDARY-LATER

TRANSITION OF A FLAPPED WING

By Carl A. Sandahl


di i : .


Li"

b.. .:.... .
e.:. .


Langley Memorial Aeronautical
Langley Field, Va.


Laboratory


WASHINGTON

CA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of
VM-ces search results to an authorized group requiring them for the war effort. They were pre-
hildy ItEd under a security status but are now unclassified. Some of these reports were not tech-
i uCted. All have been reproduced without change in order to expedite general distribution.


L 148


IS


DOCUMENTS DEPARTMENT
il


ACE No. L C08


----







7fC. co 9 1((

3.1 3) I
NACA ACR No. L5008

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS


ADVANCE C01JFIDEITIAL REPORT


V.T.D-TUI NL TNVECTISATION OF EFFECTS OF A PUSKER

PROPELLER ON LIFT, PROFiLE DRAG, PRESSU-TE

DISTTRIBUTI ON, ArPD 3OU'!D'_.RY-LkYER

TEANSTTION OF A FLA-PPD 'VI:G

By Carl A. Scndahl


SUUE MARY


Some of the effects of ousher-propeller operation on
the aerodynamic characteristics of a flapped wing were
measured in the Langley orope-ler-rc-earch tunnel. The
effects of propeller operation on the lift and profile
drag of the wing, on pressure 3istritution, and on the
position of bo;ardary-layer transition were obtained. The
results indicated that, at fixed En.les of attack and with
flaps deflected, the win1 l1i ft increased aooreciably with
increasing thrust coefficient. V'ith flans retracted, no
appreciable increase in lift 'with increases in thrut coef-
ficient was measured. Zhordwize pru-siur3 distributions at
several sDanwise stations ind jicated that the affect of
propeller operation '.ans greatest in the region irrmedicately
ahead of the oropeller' aiid th!3:t the cffet e.:.tcnded out-
board from the propeller Dil s for abo.t 2.t propehll.r- radii.
Measurem-nts of bo.Andary-l-ay-r vcloMity on tih foro.-rd nart
of the upper surface of the- wing sho,'r'd no a':?r.cis'j)l
shift of transition in the ran.-.- of thrust co:-f'i[cxrints
investigated.


T 1T2ODUC TION


As oart of a study of t'he efl'iien:y of a pusher
propeller behind a low-dr-a v.ing, 3smie measur'e..r:ents
relating to the effects of the procrller inflow on the
aerodynamic characteristics of the wing were made in the
Langley propeller-research tunnel. The data, which are
presented herein, show the effects of propeller operation









NACA ACR No. L503S


on the lift Df the wing with flaps retracted ard deflected,
on the oressuire dis tribu'tion, en the section orcfile drag,
and on the position of boundary-layer transition on the
u-per surface.


APPARATUS AXD TESTS


The general arrarcgemenet 3f the model used in the
present ii.vesti'.gtion is shown in figure 1 end the r..odel
configuratlonc, in fiure 2. The .;eorr.etric character-
istics cf the model sre ac follows:

Wing. area vwit.i flai rctrscted, square feet 77.27
Wing:i sc n, feet . .
Wini- chord with fla1, reetrcte fet .. .932
aspect retio . . 5.
Airfoil mectioni "ACA 6 5,-420 ( aprox. )
Flap chord, feet . . 1.32
Pro'eller uien.eter, f set . .0

The wing '::as constructed :cf wood covered with fiber-
board. For thn tests to deter-:ine boundary-layer transi-
tion, the winr '..as carefully srnd-d and waxed; however,
fcr the other tests, including the :.ersurements of profile
dra -, the wing 'w*s considerably less reoot}:, particularlyy
at. the leading edge._ Full-soan leFn2i,. fies' of single-
slotted, double-slotted, and z:'lit ty::es -were used with
the winr. The nbcelle was fsirjd into the having .nd no
-rovisirn was rmade f1r Pir flow' thrDur-h the nacelle.

The three-blade nroocller with a h-foot diameter
wEs .a Ham.';lton-ttandard 6101 dci-=n of modified Ditch
distribution an:d right-hand rotation. (Sae fi:. 5.) The
rro-oller L.'s driven b; a v r-iabl'-s peed vPri ble-frequency
induct'on motor rate-d t 70 hours -:-ooer at C000 rzor:. The
r.ro )ller blcd1s ver12 zet at 22.5o at th- 0.75-r;,diu:
station. Th3 c:x-.mairA 'ro)eller rotational seed was
,000 r n m, and tne n.sxImum v'irdi-tur::.el spread was JO miles
per hour. Tunnel s'oe3ds low.r tfcn the rmaximumr were
r.ecsssary ir. develojir.g th hi--her- values of thrust
coefficient of these L.-sts. The range of thrust
coefficients ussd wFs extended to values considerably
hi.grer than tnose of normal flight in order to accentuate
the e-ffects of oropeller operation on the aerodynamic
characteristics of the v.ing.


C'.:FIDE-N!TIAL


CONFIDENTIAL








NACA ACR No. L5C08


Lifts vere measa:'ed over a ranse of trust lo&Eings
at flap deflections of 00 O'0, aiLd .0 and at ronretric
angles of attack of 0 5 i Ild -. Pressure distri-
bution, profile drag, and ocundary-layer transition were
measured only with the flap retracted.

The section prof.le-drag coeffic-ient vcs measured
at three spanwise stations in the vicinity of the propeller.
(See fig. 1.) The lnimted space between the vins and the
propeller necessitated mouitinr the rale i -,mediately
behind the trsil ng edi-e as :hovi- in figure i. Both
static and total pressure -"ere imea ured.

The pressure distribution over the wiingE v.as measured
with a pressure belt constructed of O.OLOC-inch copper
tubes soldered together as rho.-n in f-' i.re 5. The excess
solder was scrsaed from the surfsAce of the belt, and an
orifice with a diameter of 0.02)0 nch ras drilled into
the wall of each tube at the desired cl-ordw!se locations.
The belt was then forced to thLe 'vifn section and r.cunted
on the surface.

Bountdar,-lay:cr t-ar:sition was determind from !r .asure-
ments in the boundary lyer over the i'orward 60 percent
of the upper surface of the wving at seven spanwise sta-
tions. (See fi 1.) The total pressure in the boundary
layer was measured with o.O0:0-inch stainless steel tubes
flattened to an inside height of O.00; inch. (See fig. C.)
The geomretric centers of tie tubcs were set 0.'11 inch
above the wing surface. The velocity in the bounaery
layer wvas calculated by using the total pressure in the
boundary layer and the local static pr-essure p-revi ously
measured with the pr-srure belt.


S Yl', P.O LS


CL total lift coefficient of rwi- with prorpeller
/Resultant vertical force
operating --

ACL increment of lift coefficient due to propeller
P thrust inclination

Vertical component of propeller axiel force

q0S3
CCTe s Din aA
LCC,..; ..C FFIDEF TI AL


CONFI DE YTI AL









NACA ACR No. L5CO0


C r.et lift coefficient of wing fCL ACL ,
L T LT

Cdo section profile-drag coefficient

(/ectioln ro-file drJrs-



c effective thrust dis'c-loading coefficient based

on propeller dis' area TD
FV D

Te effective thrust, pounds

D propeller diameter, feet

Vo free-rtrear velocity, feet ner second

u velocl r.y in surface direction inside boundary
layer, feet per second

S wing area, esuare feet

o ving chord, feet

P mass density: of air, slugsper cubic fodt

a anZle of attack, degrees; -essured between thrust
line (coincident vwth chord line) and relative
wind: corrected for jet boundary

6f flap deflection, degrees

x distance from leading edge of wing parallel to
chord line

y lateral distance from plane of symiretry

/V 2
qo free-stream ynamic r-::ssure (2Vo

p local stb.tic pressure on wing

PO free-streamr stqltic pressure


COT;FTDEI:TIAL


CONFIDENTIAL








NACA ACR No. L5C08


P average chordwise pressure .tio
qo /


FESLJS 4 D DISCUSSIOI


The results of this investiPtion acre nresented in
four sections showing the effects of propeller operation
or, (1) lift, (2) chor-dv ise ard sr:nvi L o. pressure distri-
bution, (5) bcundary-lS er trIan2'stic i r. and !h) profile
drag. The d ta are expreascd in ic.n.. i:-iensi oral ncef i-
clents and have been ccrle3ted fcr t-.Lou, id-.r: effe-ts.

In a reli mirnar com risr on it .? fo''lliC th-.t lift
with Propaller operating at r =.0 c""iull ':gree w ith
lift for the propeller removed vw'ithin eyperlientLL] accu-
racy. The lift coefficient:. at ]',-. =0 -in this port
may therefore be considered tI psoro-eller-r.ovAd v.lues.

Effect of oroF'r:ell o-r o-r Eti o, on rlft.- Lift with
power on ic considered to nr"Ive f' ur 'o,! nr-cinents: ''1) the
lift of the ;:.ing at T = O0, ,2) the incrmncnt of lift
of the wing caused by operation of tna propeller,
(7) the vertical ccrrnapnert of cropeller c zial force, arid
(LK) the propeller normal force. 'lhe maximum propller
normal force developed in there tests is e-t.:'r.tjtld to be
within the scatter of ,xper-.ment'jl points. Comrrponenr t (2),
the increment of lifL, is tl.n oUtaind, bn deduct r-g c-rmn-
ponents (1) and (5) fror the neasaire- re.sultant .ertLc l
force. In e..aluating cio.oon.:nt ), thC.e propeller axial
force was assured tc Ct ea.ial to the effic tive thrust
and independent of engle of attack at a given valuc of
advance-di amerter ratlo.

Ths variation of total lift coefficient v.tith
LT
thrust disk-loading coefficient Tg is given in igu.re 7
for several angles of attack ~rnd everal fla- deflections.
In correcting the angles of attack for jet-bounsdry
effects, the total lift coefficient C, at T, = 1.0
was used. Th!s simrlificatrin introduced inccuriicies
in angle of attack' of the order of 10.': and corresponding
changes in total lift coefficient of tO.012, which is
within the scatter of the experierntl points. The
vertical component of prooeller :xial force has been

CO!FT D::TIAL


COIF DE I', TI AL









NACA ACR No. L5CO8


deducted from the faired curves of total lift coefficient
of figure 7, and the resulting net lift coefficient is
cross-plocted asa.nrt rngle of attack at three values
of Tc in figure 8. In this figure, the angle of attack
h'.s aDcrm corrected by using the totsl lift coefficient
at each value of Tc. The curves of figure 8 indicate
that the slope of the lift curve is approximately
independent of T,. With flaps retracted, propeller
operation even at high thrust coefficients did not
anYreclrbly affect the wing lift f'ig. 2(a)). With
flops ideflected, however, the lift increased with
increasing T. The increment of ving lift resulting
from propeller oposrrtinn is the difference in lift
between the curves for T, = 0 and curves for the
propeller operating in figure 8 and is attributed to
only the propeller influw. It is ncted that a British
investigation (reference 1) shows 1lurger in-rcrsDs in
lift du- to propeller -peration t-nr: were measured in
the present Investi2atlo:.

Less lift .as cbtarined at T, = 0 with the double
than -iTth the single slotted laso. The difference may
have been caused by incorrect .esign of the double
slotted flao.

Effect of oroneller o-eration on or-essure distri-
bution.- The chordwv se pressure distributic.n t several
spanw'ise stations and several values of T., Is given in
figure 9. The maximum observed decrease in local ores-
suire associated with pro:eller operation occurred near
the trailing edge at = 0.20, the point of measure-
ment nearest the thruLst cent-r line. The. p urssure decrease
at 6f = 0 was aptrox'imtely the sarre over the upper
and lower su-f.ces, an indication that there was no
aocreci'-.ble change in lift. This result is in agreement
with th.- results of "he force test rliven in figure &(a).

Frcn figure 10, in which the average chDrdwise pres-
sure ratio is plotted against spanwise station, it mny
be noted that the propller effect extended outboard to
S 1.0, or about 2.5 propeller rc'.i from the propeller
cx
X5is.


COFI DEN7TI AL


CO FTIDENTIAL








NACA ACR No. L5C08


Effect of propeller operation o': boui.nd riy- layer
trensiticn.- The ratio of the -ailo.i y E a constant
7T RE-TO.011 in.) in the bour.dar:, la-rer t, free-stream
velocity u/'Vo is plotted as a function of the distance
from the leading edge z/'c in figure 11 for several
thrust coefficients and test veloci ties. o aporeciable
shift in transition associated with ororeller ooerrtion
or with Fejnolds number was 3reas'.ired. This result is
in agr emrent vith reference 2.

Effect of ororeller ooerat ion rn csct ion pro-file
drag.- The se.tton or.of'ile-i.gc ,-eff'.ent was nra'ured
at thres soanvise stac'ons i.n the vicinity of tihe pro-
peller. (Se fig. 1.) The vr.ri-tion of s~tiocn pcrofile-
drag coefficient with thi~ust cis"'i-lo LinrF c'ocff ci'ent is
given In f.iure 12 for tl-r:e testl vel.:- t i s. The i father
high orofile-drrJ coefficients -met-sured st 7, = 0 are
attributed to surface rou.hness ner:r the. lediin2 edge,
which presu-rsbly caused- transition to occur nuch farther
forward than vith the 'hihl polished surface con which
the transition mearur. mrcnts of figure 11 were ootjin.ed.
Larger increasess of section proftle-lr:g Doe efficient
with increasing thrust coefficient occurred than c.n be
accounted for as increased skin fri-ction dur to the
increased velocity in the propeller i nflov'. These
increases in drag cocfflcii.nt ar- :,roJabl,- due to the
action of the lo.w-.-ressui e r-eion in front of tne pro-
poller in drawing low--ener.g- boundary-layer :ir from
other sections of the wing toward th;- sections aheaLd 31
the survey rnke.


CO PCLUST T i'T


The foregoing rnaly-is of masa urements r : -de to
determine the effects of pusher--propellrr o.cration on
some of the aerodynramic characteristics of a low-dr.g
wing with flaps indicated tnatt

1. At fixed angles of att;c':r r-nd with fl'ips deflected,
the lift of the wing increased appreciably '.. .'th increasing
thrust coefficient.

2. Changes in rress-ur.- disttri but on over the wing
caused by propeller operation vrre Isrzest iru.ediately
ahead of the propeller and extended outboard to approxi-
mately 2.5 propeller r.dii from the propeller axis.
CO'tFI DENTI AL


CONFI DEFT AL









NACA ACR No. L5C08


With flaps retracted, no apprecitble change in wing lift
or span load distribution was measured.

3. No appreciable shift of trErsi tion with varia-
tion of thrust coefficient v.&E mc.E'sur3d.


Lsngley .e'rorial AeronautIcal Laboratory
National A:ilsor.- Corrnl.ttee for Aeronautics
Lrnglsy -Fisld, V8.





















REFE E C "ES


1. Smelt, P., and Soith, e-.: Lote on Lift change Due to
an Airscrew mounted behind a Wing. Pep. No. j.A.
,13., British F.A.E., Dec. 197S, and Addendur-,
p'. Fon. 8.A. 151.-a, A)ril 1935.

2. Hood, M.anley J., End CaydoE, 1.. Edward: Effects of
Propellers and of Vibration on the Extent of
La:drL;rir Flow on the 'N.A.C.A. 27-212 Airfoil.
"ACA ACt, Oct. 19'3).


COCTF TDEN TIAL


CONFIDENTIAL








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Figure 3.- Plan-form and blade-form curves for the modified Hamilton Stanoard 6101 propeller.
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P, section blade angle.






NACA ACR No. L5C08


CONFIDENTIAL


Figure 4.- Wake-survey rake installed between wing
trailing edge and propeller.

CONFIDENTIAL


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Fig. 4






NACA ACR No. L5C08


CONFIDENTIAL


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CONFIDENTIAL


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NACA ACR No. L5C08


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UNIVERSITY OF FLORIDA
DOCUMENTS DEPARTMENT ,,.
120 MARSTON SCIENCE UB
P.O. BOX 117011
GAINESVILLE, FL 32611-7011 USA













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Full Text
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