Two-dimensional wind-tunnel investigation of 0.20-airfoil-chord plain ailerons of different contour on an NACA 65₁-210 a...

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Material Information

Title:
Two-dimensional wind-tunnel investigation of 0.20-airfoil-chord plain ailerons of different contour on an NACA 65₁-210 airfoil section
Alternate Title:
NACA wartime reports
Physical Description:
19, 37 p. : ill. ; 28 cm.
Language:
English
Creator:
Underwood, William J
Braslow, Albert L
Cahill, Jones F
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:
Aerofoils   ( lcsh )
Aerodynamics -- Research   ( lcsh )
Genre:
federal government publication   ( marcgt )
technical report   ( marcgt )
non-fiction   ( marcgt )

Notes

Summary:
Summary: An investigation was made of three interchangeable sealed-gap 0.20-airfoil-chord plain ailerons of different contour on the NACA 65₁-210 airfoil section. The three aileron contours tested were the true airfoil contour, straight sides, and a beveled trailing edge. The effects of aileron contour on the section aerodynamic characteristics of the airfoil and aileron are presented herein.
Statement of Responsibility:
by William J. Underwoood, Albert L. Braslow, and Jones F. Cahill.
General Note:
"Report no. L-151."
General Note:
"Originally issued December 1945 as Advance Confidential Report L5F27."
General Note:
"Report date December 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 - 003600239
oclc - 71016131
System ID:
AA00009387:00001


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Full Text

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NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS


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WARTIME RE PORT

ORIGINALLY ISSUED

December 1945 as
Advance Confidential Report L5F27


TWO-DIMENSIONAL WIND-TN9ML INVESTIGATION OF

0.20-AIRFOIL-CHORD PLAIN AILERONS OF DIFFERENT

COnTOUR ON AN NACA 651-210 AIRFOIL SECTION


By William J. Underwood, Albert L. Braslow,
and Jones F. Cahill


Langley Memorial Aeronautical Laboratory
Langley Field, Va.


WASHINGTON


'WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of
: rBsearlch results to an authorized group requiring them for the war effort. They were pre-
O l under a security status but are now unclassified. Some of these reports were not tech-
qiaite~j AUl have been reproduced without change in order to expedite general distribution.


L 151


9, "


L- o. L52
A C Ho. L5F27


DOCUaNTS DEPARTMENT


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710 r ? I


NACA ACR No. L5F27

NATIONAL ADVISORY COTITTEE FOR AERONAUTICS


ADVANCE CONPIDEI'TZAL REPORT


T'.O-DT i.ENSTONAL V. ND-TUVIEL I VVSTIGATIOY OF

O.2C-AIRFOIL-CHOrD PLAT:' AILmFOI.:S OF DIFFEEiiT

CONTOUR OH AI, NACA 65--210 A"PCOTL SECTIOi

By 7,illiam J. TJUnrerwodr' Al;: rt L. Braslow
and Jones F. CO. i 11





An inv-stigation wars oa r .h 0. three interc.-an-eable
seal.d--ga 0.20-airfoll-.cnr.'- olain ailerone of different
cor.tour on the NACA 65,-210 airfoil action. The three
aileron c-,ntour3 test-d ,,:re- tihe true airfoil contour,
straight sides, an( abeveled trailing i .e. The effects
of aileron contour on the secti.:n aerodynam-.iz cnaract'er-
istics of the airfoil lnd aileron are ,:resertc.d hsrein.

The results of the tests inicate d that thicreninr.
or beveling the aileron trailing edge by th-. amount
invest)igt.d vrould decreas- th; a:.llror effectiv:n-ess,
the rate of change of s-ctIon lift coeflicient with
section snile of attach,., an-d t l.. .sax,!lium s3?ction lift
coefficient; would increase u-ositively the rate of' change
of section hinge-moment cocffici-nt vith t-th section
angle; of attack and aileron rj;fl-ctin;: vwould shif'.t the
arodynamic center forward .rind would c.us3 no s rAif l-
cant change in the section profil--fr : coeffiicI .nt with
aileron neutral or in the incre -rt of s-cti-rn ottching-
moment coefficient indlucd b-. E.lil:ron defl tion at
constant lift. The balan-cing action -? th: -il.-rn ald
the loss in aillron effectivene sz caused by bEve li-.z th-.
trail1ng edge were accentuat;d by the application of
standard leading-Redge rowuahn.-ss to th-: airfo)il. The
computed c!-aracteristics of the thlre seslid it.rnally
balanced ailercns, based on the data for the hinge-
moment and seal-oressure-diff'-rence coefficients of
plain ailerons, showed arn .opre-ciable effect of aileron
contour on the hinge moments at the larger aileron deflec-
tions even though all three ailerons were corrputed to
have the same hin!.e-mor'n t slope at srrall aileron deflec-
tions.








2 COMF1ILEZiTIAL NACA ACR No. LF2.7


I NTRODTTCTI OI


The use of thin airfoil sections to delay the effects
of co!mpress' bilit: on the wingrnof modern high-porf ormance-
airola.es has emphasized the need for data on the aero-
dynamiic characteristics 3f aile2ons on thin Pirfoils. The
effects of ailron contour on then aerodynarmic charact:.rr-
istics of :.l ,-: rns hav'- bzen sho-.n r-'- vousl by irnvsti-
s.tions oC 9 ].lr'it-d numbr-ar of Pirfoils equipped with
control surface Sin'~cn vry little sr-ctljn a3rondynamic
drts are avci ladle for ailerons or: thin NACA 6-series
airfoils, tests .?re ;rIFr 31 sj ACA o6- -210 airfoil
equilocd ',i. th three in"terzti-n .eaLle sealed-&ga 0.20-airfoil-
chord p.-lain a≪-arns of different contour.

'The nvestigstion v.as ,'.7.e i.n the Langley two-
dirm:ri-nrinal lo;w-ti:r.:'ulene nr ssi.ije tunnel. The three
ailerons tested differ only in contour and are designated
herein Es ;rue-cort.nur, strai,"i't-sided, and Cbveled
aleron .s. The hinge rform-nts a.i effectiveness of the
aileron and the -itching-mo-,ient and Drofil -drag char-
ucter'.stios of th.e sirfoil ware dEcte-rr.ned. Tests were
made with the airfoil surf.ia, Ra~cdynar'.icClly smooth and
.with ste.n,.lJrd rouhn3ss aopli. _d to the le:edinc e, e of
th_ t"rfoil. Tn:- diffcrentil nr-essures across the
aileron s-:al were obtainr-d i'r use in calcalj-iting tlhe
hin.7j-'-omTnt characteri sti-s rf aSlerons having a.ny
a&rount of s3aled internal J;jlsn.e.


CC'F~FI':CIEFT' AD CY.,'EOLS


The cncff ii--nts ard s-7rl'bols us-l- herein are as
fol l":s:

0C eLrtPoil section lift oneffle ?nt -


co airfoil sezctisn profile-dr?. coeffiient


Cm ci r-foil s action pitchln -ro:r'.nt coefficient about

quarter-chcnrd roint -


COp 0 ; _' -. T IL








NACA ACR No. L5F27 CO'FTDES!TIAL 5


Ap/q0 se al-pressure -cifference co3a"fic,.ent; positive
when pres3sire b-l-on sa.pl is greater than
pressure above seal

ch a.-..leron section h i-e- r',orflCent coeff.iient based
on aileron chord -- -i:


c.. aileron section bij.ne-'-r-r.:t ccefflcient base:l
S/ r/ h
on airfoil chord --)


whe re

Sirfoil lift per un'it spe.

do airfoil profile dra. .r urnit sFan

m-1 airfcil nitchn'.ng :-,o,,ent per- unit s-an

h aileron hinge ncm:n:t p"- iunit Spani ~siLtive
whlen ail.ron ten" s to efl -ct d,';..nwar,:i

c chord of airfoil wi:th a.iler:,n !r-utral

ca chord of aileronr Dohind hfr.n .xis

1I 2




P frec-s trn-2 de ns i t -

and

ao airfoir l suction arntl.- of .ttacr.., d r.';-,

5g ail-ron d-fliction vith r:spo.t. to a.irfoil,
dc.gr-es';. ::oritive lv: li ftr.a" in: -i''"' is
d 'l c tec% dowr.-ar. ; a'

R Fsjno ds rnumbr

/6cN

CONFIDE ':,'TPAL








NACA ACR No. L5F27


crn
a za






c


1.-









Ca o
.5



-ow
O


/6 = a


Sler-on se:tion1 effect-iveness par-i.eter


r.ncr-mr.nt in airfoil secti-:n an,.1:- of attach


increment In sileron d.3flcti.cn


Ga-i-ron seetizn efrf.':.tlvTess parameter
tr-ti'3 cf nrcrs'nr.t of airfoil section
.r:l- of ?ttack' to :ncr-em3nt of sil.ron
dcflectior. re-qyuired to rsint&in con-
ztent lift co.fricient)


CO,'TTD'TITAL


tao


( a.6 =+200


CCOTFIDEITIAL









MTACA ACP No. LI?27


chyT total ---a in stead:; roll

n r-soDonse oramet_-r ('referi,2nc 1)

ch) i.nce"er.ent in aileron seot-,crn hir.-:-r.,:.n t coef-
) ,5 f".ci ,nt dJu: to a c ron refie tion at a co.s-, c.r.t
section ,n-le ,'f attai & .

(Ach ) --inor ,:-nt of .i ler.r- -c .o;- hi r.eC -..,l.::nt cO-. -
if ic n c.ue. to .h- r.7 z in s.ctioin anr.1e of
ttat'-. at constai .i: rc n tiC?':n

-AC ;- ,ncre. .cr t of tc. 1]..:,?:] 3tion1 i rn -!. or'.-nt
"L ,cLoe f i.L i i: ?rt 11 L'- : 1l


P- r-.on s 2t rn hF : -: c rt r s ra ter



Ths cauo:crirts to ocrti al i.r-* v ti'-ves t-not- th-
variablts held constant vhen the ,crtil i lri ,ativ.-s
were t'l 'eri. The. d eriv'ati v s. vT.-r' v -:a? "-:-i ~t z'r'o a.niLe
of attack and zero ailre 'n o f]- i,:n.


;.OD .L


Th"1 mode 1 -=a 2.- inch che:i and a 5.'.-'n h s-- n
an,' was constructed of lsTrin: tI d .* .- -~ n v'it, tn: xc r- y- -
tion of the nterh-na ;Tl:le ." l'-ons, .-hch -ere .or structed.
of solid .ural i r. ) Or ir. t o the .'.CA o.-.. ir-
foil s action c.tre :iven n tail 1.

T. thr"e as- ron s I-e: ts,.-: j .- 2
and consist of the true airfoil c o.: ur' str' .-it .ides
and a beveled tr'irl: cge 'its ri" fts ci tl 'r--
cr%:-tour Pileron 'w.r-' the ss.ne as t o-- '' n' ts 'e r in
table T for the tr-i in -ci .: -art *o th- I;A:A-. c65-, 1 _ir-
fo-l section. Th-. contours of t'h. trS1i :- t-s'.ced a- r.:
beve-led -ilaerors :.. r :r'".d :,- st -::.i t Lin--. a s .own
in ii rure 2. A r'.xiJber cose.al. .vy: *:... at th ':. 'oo at the
nose of the ailler.jn.

For the tests of the s.r-'oth :. rfcl. the od,..l was
finished. vith Io. .'."3 c:-.rbL ran.: am n ser to ,rocL.e s::-r -
dynamically srroth L.rfacLS. F the t- ts o". th.," air-
foil with stsn'eard leadin,-ed -:. r-oighn. -ss, the ro'il
OCOLTIDETIAL


CONFIDE'TI AL








NACA ACR No. L5F27


surfaces were the same as those of the smooth airfoil
exce-:t th.t 0.011-inch carborundum grains were pliedd
to ooth 3.irffces at the leading edge over e surface
length of 0.0c measured from the leading edg3. This
rouihnes3 is defined in reference 2 as the standard
rough.ess fcr a 24-inch-chcrd model.


APPPAATU3 A/D TECTS


lThe lift, drs .., er.3 Ditchirg *!oment cf the model
were measure' b' t. r-ethcds doscr.ioed in reference 2.
Tnh- aileronr hS.r.ge-norren --ssu. re:.-ts w-re -ad'ie v.ithi
electrical-resist.anr e str -.in .:'_Cs_ 'ounted on the beams
that suro.orted the sile'ir.:. "h:Ls method of mounting
eliminated the poss" biit-.,. of iritir.on due to the use of
beariri". -t the ailrcn hr...3 ays. The pressure dif-
fevrence acro-s th3 aileron s-jl wi.as :r:easz .i.r with surface
static-oressure orifices locatr6 iiislde the gap above
and below the flexible rubber- CE s.

T'est.s of the t.nodel -'ith each of the thr.- ailerons
were r'ade in the Lanr.-ley trva-:.'dimnsional low-,urbuler.ce
pressure tunnel at iFynolds n~rcbers of lx 1Ob and
9 x 10' and at Yach rnurrbrs of 0.'7 and 0.17, resoec-
tivety. The tests incl.del d .:'-.sureenrts of lift, sileron
hin~.-e .nor"-nt, Pilb-ron balan-a pressure, ard airfoil
pitching. rcr.?r.nt for e cbh aileiron deflected in rnore-
ments of ', b-'tv'een -200 Pnd O' Dr.8g seas irmcT-nts
were :as,- at both eynolrds nm.bers through the comple.te
range ef aileron d=tle3tcin for th rrod-1l with the true-
contcour a.il-ron ani, for the rmodels ',ith the strai,-ht-sided
and b -v-l.?d a-ilerons, at a E-;'nolJs nurbr~r of a x 10
and 6a C r:-ly. In addition, the -oCel ,i th each of
th? thrEi-' aill _rons .:-.s tested at a T ,e-n ; ,lcs rui'ober of
r, x 1 -, t" tr.nd r r 'ughn .-:n ". the c"! I.. _tn
ed,:- of th: f'.rfoil. Lor to: r.ir 1 ; th l- '-dinj-edge
roughn :;, only lift, a.lern hiJn.'n '.1iomcrt, t ind ail..ron
balan;nce nr: s-ur "-~: -"1- sured th ou t1nu the ran.e of
ail.ron '.1'flecti. o:ns.

T'- I ollI'! n.; f[ct. t r v. -r- .?,oli I l to norr.ect the
tunrinel ,j-lta to free--.i.r ci'n.iltiorns.

CL = 0.97'' c.

do = O.-l o'
COd D AL
C. 0!7 1 21 ,T'i A r


C -,PI DENT1IAL









UACA ACP FP. L5F27 CONF IDE TILL 7


4 = lO.O6q ,b

c.0 = 1.015a'

where the pr-imed quantities r Eonicre. t t!e- vih l:e r.i' s5.irr-d
in the t unnel. (refer.en e 2,


P<~ vT'TT i:' LT-i


For use i onalrn desi-rr, b-.sic sectic:-. dat. a re
presented for a ran-'e cf a.l.-ron 6:flectlon in figures 5
to 9 for tne trT-ue-ecntoui al.lero-., in figures 10 to 13
for the straio;ht-s'ded ailercn, and in figures 10 to 21
for the tev.eled aileron. These figs.ues include d&ta for
the airfoil with seroJ -r.ricall-' s..oth surfaces and ;ith
standard ro uhr.ess orolied to tno lea:ir.g edge.

These bs'sic sec ti. n dn -. .d"- be 'ise- to predict thi.
section higze-moma- t ohM r-rste-i':.s t.. S cs of 2ell=r-ns of st:,ilar
contour and chord with any 9.ogricunt of S:.aled Lnter,.. 1
balance by the follcwin., eQiutions"



a0 2 i( ) *l


Ch i + 'h-h '2 "
c" 2lrcei ilrer Ln _. i .Cil-rcn

where

Acha increment -.: aileron sP.cti-:, !:.iMc--C"'e3rc.nt coef-
Sficient ,rod'..iced by sr, i r.tenrn.l-bal-.ran.e
arrange.nPr.t

Cb chord of overr.en. fro-. ri 1: rc n 'irce- aa'is to
middle of ':-sled g e

fa .hord of aileron btehin.- rin, c axis

t twice nose re-dius of oiilin aileron


CTT AL I3IEi-T!-7









8 CO;FI D irTIAL NACA ACR :o. L5?27


Equation (1), in which the overhang is assumed to extend
to the middle of the gap, can be used for determining
the overhang romennts of sealed internally balanced
ailerons of normal configuration, that is, ailerons for
which the overhang ext-ncs straight forv::arA Into the
brlanc- c'1ia:.ber an-,t the sealed gap width is swall.

The dc.'--at obtr-inEd at 9 -.Efnolds number of 1 x 106
arc not so azcu.r te as E thos-? ct-Cti-Lrd at a Re.n.r.olIs
nur.ber of q x 19 beDause of 'ih S-,&all dynamic pressure.
Thle results tor the lov, er .er:-nolr nur:mber, ho"evSr, are
believed to b: useful for irnic.t'ir:r qualitative effects
r Fem;ndls rnumnb.ri on~ the s-Lleror characteristics in
66 6
the rn:--- o'f Peyniols nl:r'br frc: 1 x 10 to x 10

T;"- effe-cts of ailEron cr.t.ur O n section char-
acteristics -r-e or':-ared b.: ct.b.ans of section cera.icters.
Vrari to!r.ns of there oars- -.-t _and cceiffici'ents with other
i- p-'e,.n st vi ari.-oles .*:"e o- ? N.atot. in gr:a-pihcal oan
t-bular- for'.

Th' f 1 owing -discIuss1 on ~refers to the dets obtained
-at a tF:--hnolsC r.ULmber of x 1 iCl %'i th the airfoil s rfaces
arodynri' ic &ll:, s.ioct ur.n l ess ct:-r-wise stated.


DIST J S7 I

Aileron Effe? tive r.-e ss


The sffgcts of ciil.-rcn ocrnt'.;.-- are sho-.n int ta';le II
for th- a:.l:rrcn section eff..2ti v.sn-E s paramater a: and
fo-r d in fi 22 i rich is olotted against
&^ st co~n7t nt cl.t c c'. g r -s.- .-, t.. -rni ling
.ed of the saileron resi ltd r. a rl-cre ss in both G.
sa: c ,. i ''I'. f t' ff ecti. .'' ve ss Ds.r-a1ter a.
of r;F-q: ":f th:- at-.T : ler (c, s t cstS v' as slightly greater
th~~s? the -..ale- (- .1. ?) ot1 cini:-d for .a .2C3 plain aileron
of tru. -.ar ? 1 contout 1n s.n ".'T 20- irfoil section
(r.f:rea e:- ). T" '- =r .rc .t i lo in a3 -ue to trailing-
ed.Le : .'f:fiz,-a -cns to the tra-3-c.::,nt.cur, ailzron is -iven
2i -' l? ';",ll7 i'r" t Ci e ;:


C01TE DS: TIAL








NACA ACF No. L5F27


Sirfoil
Ai lron
--
S!rooth Fou.h
___. -- F-- -----I--------1
True-contour C I .7

Straii. t-sd1ed 1.5 i .' 7

c-veled 2.5 2.1
0

The v3al1e of' tin eff. 9 i.v-~.~-s ?9. i t.r r ,f-- ,
o '-/6=i200
when mn:nsured over c rt:g ot C .l ;on ri .-f :. on -f z2'
at a constant seoti : n lift co:-fY'' lr.nt of 3.20 was r.; ter
f.r tihe straight-s.ded E-il ro:i o : ..t'r. ni'irfo' 1 7:ith r .. t'. h
surface or vith lec,.in.l-ed o riouT-r..:cs then for the other
two ailerons. The vs'ue of this g r':-. -tr for the beveled
alleron vwas P~iso grest'r thIn f r the' true-rcntour ail'r on
with the .irfc l z-1o3 r]- it w' \s3 'o'- --r r1.it!h 3*- sn ar
leadinri-.ed.. rou-rlLt ss a.oKl t.. th irf i l. i
increase in the secti~ '] life cc '


a
to decrease for the true-cjontcur aileron sndi to incre .se
for the straiht-sided d ard bev.l- ailerons. The3 \:.;1

0of -- Ior theC oelcb'Ld eil.prcnr is Louection-
\4c a/ ca=o2 os

able becaus- -'f a ,:.- in the 1i.ft curve tt = o0.C
6a = 20)' (f .' lo(b)). T'le a lror efirct' ve-i.es-
deere .as-d sl ightl v.ht-n the -?ylls n rt.e r -"as
incre3Ssed fromr 1 X> 13 to 9 I ~ 10. a? ho','n "n tatbe -I
and ft iure 22.


e.-. ilrorn .T : t

Section charcr-iter st s .- 'T.L eff.et of pille~:rn
contoir on vaq i- i3 l 'or s tiCr L.i re-r, -.ne-t ? .r.ete rs
is presented in tRaol ~. h-."a:--.. s in the ceron contour
from thc true cir -oil t .' i.' ..*. : stra3lht si,.es or to s
beveled tiailinL 3ac?ae ;ncre"sdcl th; v.!.uc s o* c.h
and chg. positive eai, It is c.vid".rt from' fi. re 17(b)
'-6


CONFIDEI.TIAL








NACA ACR No. L5F27


that the exact value of h at a = 0 for the
ah
beveled aileron is corsidarably less than 0.0069 as
given in table II but. because of the shrp changes in
the variation of c- vi th a near a section an.gle of
attack of c0, an avarL.e .lcope ,rs used for ch
'a
bet:Pi-er. vai.es of of a -20 cnd 2'. An increase in
the "-,ynol.fs. nr-n.1er frcm 1 x 10,C to x 10 rovided a
positive increase nr c for ell three ailerons and
-'a
in cOh for the b3V,:ld' a'.ler r.r oanl- (table IT). A
co,;:oa: son of the aileron h .n::?-rr.'o,.'nt character sti. cs
for a Peyr.,-lc r. b- r of x 1.'- f r. L 11 and 17)
sho'se tbh t es tiie al lon aans L'ick':'.e.d and beveled
nar th.e ':.r lin- e3r, :b:."u t ,chane: si.n c-, occurred
-'n t~e lo;w n-.'Slec-of-attacl.- ran.e.

A cop'srisjn of figures 17 -.nd 2C shov.s t:.t the
abraut chi-ngr-s in. c, for Lit? hevl.cid aileron disappear
lvhen rou-Thr.ess !s a-3lied to th"e Lc e;L6ng ejde of the
airfoil. The hin---om.ant chlm'-rctr:-stics of a beveled
aileron, therefore, ms.y be ssnr.itiv. to wi'.r.Ing-surface
rcu n-re ss.

riata show nk the ar'. tion of the inoreents f
and ch, wt t chanTes in trali.ng-e-f.e angle of various
ailerons on smr-e I'ACA a'trfol .ectin ns sre giver in refer-
ence L. *:-tn bt.se3d ..n the c-,an re in tra'ling-edge angle
froi. the true-sirf il contour, the :ncre:n=nts of c,. and
co for the strs;it+-sided and bevi ield silerons with the
'5
airfoil e ith- tr s5:rothi or vi tn s-aniard ro.ughness aonpled
to the 1.,jin--edgE fall nitnin t-j e_,orr.rental scatter
of the d:-lt or referE-nce 1.

The eFffe'.: of 'eji-nol's nb.-be-r on nq can be
se.n in f.'igure 22. Ar.,:n..e.s. e in the Reynolds rn '.ber
from 1 x 16 to e x 10 c-:re: -d t: the ava'Tlale pressure
differen:p s:- rMs th, allcron s1i.

E&.as fO? C.:zl.r rrc--.):Lon. '7. rate c.f roll gornerated by
the ah:le--or hiLs an 2a'por'Erit elect o- the hinge r.sment
tec'us2 the r-ate roll zJ]t:r: the rean ar.,n- of attack
at ..:hich the iilernr, is o-r-.rt nr.. '..r cor,. o ri son of
aileion-' froT .sti-', i *'L, tle.r3ie, th alilron hirae-
mo1men-t charazteir.i ics are usually determined by use of


3:;VI D'L_'7TAL


CONFIDENTIAL









NACA ACR No. L5F27


the constant-lift concept, that is, thz assumption that
the aileron portion of the v:inc acts at constant lift
during a steady roll. In reference 1, however, Gates
end Irving I;ndicated that the co.istan-11 ft con-cert
overstress~es the ilrort;r'ce of th h in,:-Tj-inent para:neter
and gave the equation for tlh, rate- of -han.ze of the
arirge- iotent coefficient with allercn electionin Ln
steady roll .s


Nq ( )


rather than

,a -Cha,\
"T = 1+ ')+
h c h \ /


which s the equtLion for the co:'. t.t-tlit onr.:!t.
Altl-ouh equationn (5) ir nI-'.aeiqu ite 1or .co puti"n
finite-Fsarc. ctar.Dr3teristics, it 1i s t- efsctfory, for
co;ipar-ng the three asilerons o f different contour. Ina
order to sinmlify the appli cr tion of equrtion (5) to
nonlineror curves, the equation vas converted to
0T- bT



^T'W ^ ), rjr r, 9e 1c
= -



A typically vnlue of I,/ is 1i''c' f.or n in r efrence 1.
The value coorresoonr'.. to s vw:-.i il ;.-; r- Ea l& ron oi1 n ; to.oE,
one of which is a vin :- .i tth an aspect ratio of C andr v',ith
a 0.200 caleron '-.avinr. an eq.1l u1-.-nd-,:'ovwn deflecrtion
and extenrving fro1, 5 --'c--,'t .mi :ipan to the 'r i tip.
The value vas use.- i, :.uat. :. (51. The
inethod of analysis .ssed herEs.1n is considered s.iit .bl.e
for co';paring: the r-lat'.ve merit'. of t.h,-e three s-laaons.

The analysis is presented in the form of th3 .q,..ivt-
lent char-i-e in section ingle of 3tt.a.ck iZ0 requi red to
CO'FI DEIT Ti L .


CO'FTIDEFTI-.L









NACA A.AR No. L5F27.


maintain a constant section lift coefficient for various
deflections of the aileron frorr neutral. The hinge-moment
:na.reter -T ..which is the ratio of the increment
A &o/5a
in hinge--1, Dmnt coefficient in sterdy roll (equation (5))
to the .-ileron effectiveness, is lotted against the
equivalEr.t change in angle of etts.ck. The method of
analysis ta'-e into account the aileron effectiveness,
th.- hinge mo- er.t, and the possibl' -ire-ehcrni al. ad'jntage
betvws t'he crotrols c'.d th l l'-ens. c Ti. scan of the
a. leronrc nd possible effects of thre3--dir',ni aonal flow
are not con-iered eycert as .riLc ated in e 1Ption (5).
The str..:.l1er the v/alu- o th, k n..r -n.,r.cnt p r. met.r for
a 'iven value of Lc the nore advantageous the colnbl.-
tion sholiul' be for r.ovidin g A lo',wr control force for a
;-rven h?.lix angle of the vwi i; tic -
2V
r'lain aileron.- i-i order to cor pare th. plain ailerons
of different ccntour, values of the hince-morient parameter
Acu
cre plotted ag'.nst La in figure 25. Figure 23
Aa,>/ a o /
indicates that thickeni.ng ind htvling the trailing, edge
of the aileron would i -prove the control-force character-
stics of a se-led-asp 0.2-_ plin aileror. '"he s;;plica-
tion of standard roug-hness to the .irfoil causes the i-inr'e-
S ... t ...-rs .:; r ::. C res -: ..n r:,. itud-e c- iall v -il.as
of Aa0 and- to i-ncreaz3 for lprge values of Lao.

Ba ~1 ed 11 -r1cn. or cc: '- ,e1ns cf the three
ailer:n. of *ifferrit contour vitth sea.lcd internal balance,
the eff*"'ts of e...l chan-,r3 .r Lhe pressure difference
acrcvs le 'itler')n seal ar.i :hng s in *.inr. roughns'es are
i !orta:.t. a'or a conser9 U iv des3. .n, the internally
balanced t1i" leron m.,ould be a r. ro )7 tloncd as to avoid
''-:-rb l ,e I -,'- tn th ie v i h s the rou iest su.rf ce *ha'r.t
w ,."l- be /:- ted .r service., or the airfoil with
star.nrsd eiad r -.-%e r- h".-', h'c chord of overharn
cb nee. n -ary to l to bClcim E ircn o c = -0.001
was cc.":'ut-d byi ":?.is ?.' the fellow'rin e-quations:

r --,
o l/c\2 I 1 (6)
6balann, r n o 2alar.ce 2 a a /

C ID DE iTI AL


CONFIDENTIAL








NACA ACR No. L5F27


Ch = ch h a (- (7)
balance "- no balance 2 Ca ca




n ( 1 "hA



The connmted overhangs './.- 7'er? 2.556, 0.551, a and
0.396, respectively, for the true-o:..ntour, straicht-sided,
and beveled a-llerons. Th_ :.inle-r.,cnt -ocefflcients for
the angle-of-attack ard si leron--deflacti.jn ranger were
then calculated from the nota or t_.e hinge-.rr -,nt and
seal-prl.%sur:---cffeFrence coeffi.cie nts for the nlain
aileron by use of -'ations (i) and (Z). The approxiiate
lir.E tin5 deflections of the t.-ree s ld i nr.tneilly
balancc-r elleeoois of true Pir'oil r ntoiur, strtnr:i ht h ides,
and a beveled trelring ed. -e :~or -]5+0, a1, rad 20,
respecttvely. Th r ayax Ilrr-T .efle stirons were lit.:ited by
the lengths of the sealed internal balaiioes.

For comrai.soza of three s..;ld internally balanced
ailerons, :values of the h in-- -- 'ept ,-am tc.r
Ac-T
a-7- are olottec a:sinst a, i n figure 2L.
Figure Ji sho-ws t. :t tnr- str .;ht-r- d.sd pironn
should -~.r-ov de the -r.; lle. t c, l rrt r-l force of
the three sealed irte.rna. ly .' anc .l.-iron,. ihe order
of rreri+ of the three ailrnro:. chj).ed ".T.hen. the. Internal
balance vwas -di.ed o.reaus' of ,--.c. ffeets of aileron con-
tour on the available ?&el-J.erMs.re-di' erence co.f?.0j.ieit
at the hli'.p r il Jror dc fle3t-i.n3. For n vn 'Lth
smocth3r surface than that for ,,hic]: the conservative
amount of sealed i-tern,:;! belrnc wa's *.eter:=sned,
th c:.nfrni force 't-, t? r tr<. -.ht- *de c1iler 1i
vould c'an:,ce L.e least .f the '..r'? :;iler'-jns, 'Tis
smal.,l .hei-nge 'in th.e rcr.-rol for.e for the strairht-
sided aileron can be seen in figure 2L oy a comicarison ol
the values of /T for- tl.e snootn airfoil with those
a.,/A5af
for the ,irfoll vwLth 3t;ancd; i^ ":d p-ed-." rZoughn'lless.


CO'NFI DA ATI AL


CON DLEN'TI AL









NACA ACR No. L5F27


Lift

The effects of iieron contour, Reynolds n'lm.ber, and
standard airfoil lesdirg-adge ro',.hness on the lift-curve
slone ca for the NAC.A 651-210 sirfoil section with the
aileron neutral are shcvn :in taile II. A study of table TI
shows that 0c is charngd t- either rou-hn'ss or
Tieynolos .r._ t:er by 1, L. th':r. 2 :-crc:nt re *':-dleis 0o the
aileron contour. A rteduction in li.ft-curv': slopes, hov:ever,
of as.jro.. i.stel; a.r I 7 oe re.t. .'sn-.ctiva-l resulted
when the ,.L..ermln -.s crP;'d fr;r' th.- true irfo?.i contour
to str.i.:--i t side. s o' to a -.el-d trsilinr. edge.

A co~Tarisinr of figure : 1., ;-.nd so.ov:3 that for
the -airfoil vith !rztroth s-rfrcos rT.:e :'E'xi'.ir section lift
coefficient of the iAC. o -21 ..ricil section '"ith the
Rileron neutral ':-es spproxi:n.tel-. S, p.-rcent less for the
-'odel .'. th the -, tr&ai c.t:-sided or Lev 'led ailerons than:
"'it;h -he true-cortcur rA.'l on. TiS locs in Tma.xi.r.u sec-
tin ii ft .ocffi'ient is at;r..b:ted .o the change in
c mnber over' the reer nirt of tn- v'ir'oil section caused
by the ileror.-c:crtour.. Todicsti'n. omPr'isoi of 1g-
urs 7, 1.3 nInd 19 s:'iows that, for the airlfoil with
..Lnr' !uCv 1 linC-r'l rg2: rourifnl.s;ss, ths 1-ayl:ru:-. socton lift
cofi'f~lient :.-'s the sare for thde truc-ocutour .3an straight-
slded ailerors out tn.t the ~axixur..u: section lift coaffi-
lient for :.he be':el.j ~.ilerionr wa saless tha- -. th. for th.-
tru.e-cont our .i leron.


.itch.n 'o L nt

i ffct -fi ll.'-ron o.tr::our on the airfoil s*-cti on
oitchir: m'To--rt 's s!.hov in taco TI ar.d fiur. 22. The
rate of cnanrre of c -,'ih c- becotr.s ls r_-.Sative,
"."'.ich ,;c*rr!: p n .13 s to for-;::ird ?'. ft i1- t..e Z:nrodynam'r ic
"-,nter, an- the ailer-I conco.r is .cha-.nged fro9T'm the true
airfoil contour to .t-'ailrt s c'.is cr t.c E '.-..eled trailing
.-e. Ths" cran,... in aerolyn.,'i center screes with the
r:-sult.s f '-:-f.lrnc.s ~,n b. An inc r ass in th,
9R::- n.Jldj nr.umbh'r froir 1 x 13 to Q .I 10'. ha no ap reliablele
effect orn Lhe ';ratio cf c/~, .itn 5 st a constant
s.cti-1j lift c ef'fi ient o' "'.21 '' fi 22)


G':FTZlD"TIAL


CONFIDENTIAL









NACA ACR No. L5F27


Because the charges i.n section pitcr.ing morrmet of an
airfoil induced by aileron deflection are of primary
importance in determining ths lateral-control reversal
speed, the variation of the increment in section oitching-
moment coefficient Acc/,L with the equi val.,nt change in
section angle of attack required to maintain a con.tsrnt
section lift coefficient was olotted for the -hre.
ailerons (fig. 25). Tha variation of c with Aao

was approximately ihe same for the thrse ailerons tested
(fig. 25). The rate of chl;-,e of Lr,. with laL
"/ C L'. A o
is 0.0205, which agrees with the theor.ti..cl nd experi-
mental values given in reference 7-


Drag

The effect of aileron .Sontr-'r 7on the airfoil section
profile-drag cceff .?ient is presented in figure 26.
With the aileron neutral, charges in tne nileron contour
within the range investigated shrc-. no significant effect
on the airfoil section 'rcfile-dr-i characteristics.

The variation rf airfoil section profile-drag coef-
ficient c "'ith section an ie of attack a- for
various aileron deflections i.s ore sent :d in figure 6 for,
the true-contour aileron at Reynold: numbers r 1 x 100
and 9 x 10 At a Fr-enolds n:.~ber of 9 x 103, a low-
drag bucket" was realized at all sileron deflections
(fig. 6). Because the m.ijange in cc with aileron ?on-
tour was small with the aileron neutral, the section
profile-d rog characteristics of the airrcil with either
the straight-sided or beveled rilern dreflect?d would
probably be the sa?;'e as for the airfoil ,ith the true-
contour aileror.

CONCLUSIONS

A two-dimensional wi rpd-litnnel investigation was mrad-.
of an NACA 651-210 airfoil equipped .ith three inter-
changeable sealed-arp 0.20-airfoil-Izord plain ailerons
of different contour. The airfoil was tested with smooth
surfaces and with standard leading-edge roughn-ess. The
data obtained indicated the following conclusions:
1. Changing the aileron contour by thickening or:
beveling the trailing edge would cause


CONTFTDENT AL









,FPCA ACR No. L5F27


(a) The aileron section effectiveness parameter a8
to decrease

(b) The? rate of change of aileron section
hinge-rmorent coefficient ch with both section angle
of attackk ao and aileron reflection 5a to
increase positive31

(c) The r3'te of change of section lift coeffi-
c.-t .; with section tnfle cf attack ao to
dec r 9ease

(d' The "'!:lrur: sec1cn lift coefficieet to
decre ss3

is) 71?be erodylns.:rc cei:ter to Thift for.:ard

(f) Th. inc.remlnt of section -itching-;noment
0oefiicier.t inducec. by aileron deflection at con-
stant lift to refrain the same

(g) 1Th section pror'ie-C.rag cosfficient witn
tile 2i1leron n-.-utral to rer..ain subst.nti ally iunaffected
t,-:ro-G.ihut the se5t'on rg]-of-'.ttack rarge

2. The arplicstlon of r-uugChna.s to the leading edge
of the airfoil would accertuate the balancinec action of
the aiilr.on .nr. th-- loss in aileron effectiveness caused
by bevelirn the ai'.lron tra.ili r ..:A.e.

5. The 3ff ct of siloran conLour on the hinge moments
of sealed intr.rr~ll: balanc-d ailerons, as =orputed from
dots cn tie h~nge-:nent and seal-ressuressure--dfference coef-
ficients of nliin ailerone, h3oweVd n appreciable effect
o0 aileron c-itcur or, the hinic : moments at large aileron
defilctor.os evnri tnr.lih-ll z.hree il lerons were crni outed
to h.va t1-e sa~e hi i --rmcr)t slo-: ?t 'e-ll deflections.


Lan le- y I';- eri al A-;rcr.ct r rl1 T. or toro
-tionrLl .dv. 3'i'sory Cm-c i ttee for. Leroneutics
L:ng l ~y -ield, -.


C7f ID DEiTIAL


CO -FIDETI AL








NACA ACR To. L5F27


ZFE RE :"CES


1. Gates, S. B., end Irvini., F. -.: .An Anal-sis of
Ailerr. Performe..e. '652., S. i l1., ,r.,
o. .A. 62AL, 1l ti i F. ., J'ly i'-6 .

2. Abbott, :ra H., voin oenhoff, .'i-rt E., c r.d Sr.ivers,
Lcuis Jr.: cur%'-ar:, o .- rfo'i] [., ". A '
.lc. L5:0$, 1-)5.

5. Ae ,, TLil-tcrr ., J-.,. Ed E .s_ .I -a.. I. Deter-
nir itor of ntrc l-'uriee Ce i''. ;r-.:tr.:tic: froi
:;Ak! .lc.in-^Cl --;c TnL l A '. 7.. 71
1941.

4. Purser-, Psaul Endi i li, .r ?-e .: Preir..iinry
correlation rf t,- Ff7'fct3 ,. ed Trsil-g
Edges or the kin :--.'?! t O' i t.er'istic3 '3: Con-
trol 3urf3is3. N .7A 03 -r. Z1l-, 1904.

5. Cr-an Sobert ;., an-d Eolt=:cl0c3., ?.. :i; .. "ind-
Tunnel n nvDs.tiga-c'.un jf ~ii-.rtns c r. Lorv;-D-E.
Airfoil. i -ie EfTeLt -. ,.il.r'on 2rofil?.
NACA ACE I.. LAll, 13._,.

6. Purser, Pnul E,, snd Jomnno3n, irrola : Effr-:ts o
Trailing-Edge :.'o-:ficiat.eons on Pitc'.lr.,- 'nnt
C4,eracterist cs of Airifoils. ACA CB -. L[.n,


7. Purser, P..u. E., and PcYtnniey, liz bcth .: Ir.-
ririso' of ?itch-rin .?3,:tr.s r o ed -. -l'in .I -..
.nd ov Spoilers 'ind Sm.e A-'cdyni, c 'i. c ict-erist..cs
of an NACA 2'.C12 .AiLrfoil wilth Vsrics, -'--.. es of
Aileron. -A AC I.A. L12C'., l?.


CO;;:I D STAL


CO.TFIDEI'TIAL






NACA ACR No. L5F27

TABLE I
ORDINATES FOR NACA 651-210 AIRFOIL SECTION


[Stations and ordinates given in
percent of airfoil chord)


CONFIDENTIAL


Upper surface Lower surface

Station Ordinate Station Ordinate

0 0 0 0
3 .819 .565 719
.67 .999 b22 -59
1.169 1.273 1.531 -1.059
2.o8 1.757 2.592 -1.385
7.898 2.491 5.102 -1 859
7.594 3.069 7.606 -2.221
9.894 555 10o.106 -2.521
.899 .58 15.101 -2.992
19.909 I.958 20.091 5.46
24.921 5.597 25.0o7 -3 6o
29.956 5.752 30.064 -3.78
34.951 :5.54 5.049 -5 .9
:968 6.067 40.52 -3:925
-.q84 6.056 45.016 -3 06
50.000 5.915 50.000 -5.709
55.014 5.625 54.986 -54355
60.027 5.217 5997 -3.075
65.036 4.712 6.964 -2.652
70.043 4.128 69.957 -2.186
75.o04 3-49 7L955 -1.689
80.0o 2.75 79956 -1.191
85.058 2.057 Bb.962 -.711
90.028 1.527 80.972 -.295
95.014 .622 96.)o .010
100.000 0 100.000 0


L.E. radius: 0.687
Slope of radius through I.E.:


0.08425


CONFIDENTIAL


NATIONAL ADVISORY
O,.'MITTEE FOR AEFRO;AUTICS


L.








NACA ACR No. L5F27 19







0 IO 0 I 0 CO CTO
r1 I r 01 0 0 0
0 0 0 010 0 10
E I .
o 0 1 I 0 1 I 0 I "I )
I I I I I
-V E-
I- O P- I N 0 r1 1 (
.4 10 000 r91o0 a
0 0 0 0 0 0 V 0
d0 0 0 0. 0 1 c MO
S* a 1 6 -O
S0 0 I I 0 I I 0 I

I I 1 0o

o 0 0 0 0 0 0 I .
o 0 0. .1 I B
0 CO 0 I 0 I 0 I OW
II 0 irn4 I osU'l I 0 -4 4 e -
N NI N < a -
a) 11 a 0 0 I 00o ar
10 P I O I SK
0 0 0 S

N .C O NO .O 4.. OOO '

< 0 * U
o O i l 0 i 0 I
0 o -------I -*--'----1---
SI\ I C
11 N 10 N O 00 Oa 0 0G
0 0 0 0 0 0 O



4< a a 1 r-
0 4 0- 0 ii

SO
SI 0 0 g 4 E-4
n 0 1 I I a .d I a 4



0O e i
ClE ia 0 1 -*
o P 0 0
1 M oI E CD O t ti s1 0 0
0 l -o
0 NpD E4 Ml to 1 o *a o

E 0 a c. 8 5

N N cOO 43 -4
i an o 10 0t 1 i H- ,C
a *O.l .0 0
Sa I I I CI

0 0 1 N1 IO m O
Ol Pi 0 4 0 0


DI 0 1 30 0 0 *
1 0 (M IO 0 0 i 0 0'i
to 4 Io' so '0l co O os n ra)
I f M 3t _t r- t f rt ;t c0
L


a o. 1% --I %


E- NO'.M 0 N1 1..
1-3 1 0 a 000 00 nO




0 I a r: 0 O I II
M 1 10 O O I 0 0 I C

Sc a r o U' o1% 0 0 0
o0 o 0 0 l0 0 1 '0 10 0 1 10



A A 0 > > *


gg gr in cn a: toEn Mo V ar A
E6 b]------ ----------------------------






0 s0 O a ^ \ B
0 00 000 0 0 0 0 0 0O








NACA ACR No. L5F27 Fig. 1




















QJ
,a













-Li

on

Sm



a 0









.. "0

,:'..r. ::0~,~












': ),...
,
:. .
b: i' I ,'
........ .i c


::: :i=
.rl~LL s~Dn*I,,-- 1
: ?.; .. r


~E~l~ i~ll~s lsll9s~ l., '-t






Fig. 2


NACA ACR No. L5F27


CONFIDENTIAL

7-- .003c


(c) Beveled aileron.


NATIONAL ADVISORY
CONFIDENTIAL COMMITTEE FOR AERONAUTICS

Figure 2 .- Sketch of the three sealed-gap plain ailerons on the
NACA 651-210 airfoil section.








NACA ACR No. L5F27 FiE. 3a







O



r4 -

A ..

ir i-




7 J




-1T

.., .'- .1,
_, __77
.1 4,1 J. 1.5










N.; -I : _I!-
S- N I I

F .
!o




















]r 1 7 ,






















*Be6on abgle of it at.k, o deg
S. 1




















1 -(a) R : 1 1 .0





airfoil c to1. Sentn "DT 8 8 and 80.
io -15
-10

i1 -5








-0


Z _7 _- i Jl-i CONFIDENTIAL CONlw-TTEE oN AMMITS








LIrfoll contour. 'Meta, 'DT 847, 849, and 850.






NACA ACR No. L5F27


'CONFIDENTIAL


S True contour


I --w---2-----------
4_ _-_ -





I. i ,- -
10
j i' II T,







--0 -



--- -----









.- .-- --- -
-20

-10
-5
3 c FA
: I,, - S / ^ ^ I
^- b,,_ ^ L. .,l^ *Jf --. t^ -. _-. _
^ -' ii- ^ : ^ '1' -! -^ :1/ -J _ _
^^^ ^^L^ -^ _^_^^_:^.









ii- i -- __ _~ o&^f:l-:!^^=r: _L _
|r^ :===i^^aE^ ;:;^
^T .,,:!*. *'*' '^ ^ j-i-^ -'.fl.*^- --- 15
^ 1 J -- -- -- -- w -, -^ -- J -
- S __ ^ ^ ^ '_ ^ J 2 _

feL jI Ls ^^=&'-r=::ljr:z:
n"! _|_ A IN LA VS R
ii r. | | O FD N IL "-'f0iTE ITC


WW:f.h I1 \
slfc-H I I I1 i


-3lk I I I A I I I I !t I 1. I
SSection angle of attack, a. dog
1L' I_ r L-I 2.ILJ[1 1.1
(b) R = 9 x l0.
Figure 3 .- Concluded.


I1K a v! '1 r i r r m mI I 1 1= r 1 .


. .. l l I


1


Fig. 3b







NACA ACR No. L5F27


^^--ri6----^^-^-- i^-1------ -- -L--i---------











I

44-


:---I
















E5T E7 X '20
S4 --. -.-
a -15





















. .. _. CONNI T'E rj1 AE-t OIAUTICS .
-_4





























(a) O = 1 10 .
Figure 4 .- Hinge-moment cbaracteristics of a sealed-gap 0 20c plain alleron of true
airfoil contour on an NACA 651-2l0 airroll section. Teatas, mT 847, 85.-
f7-
















S.-1 ....... M










airfoil contour an an XACA 651-210 airfoil section. Tfttt, TDT 847, 853}.


Fig. 4a







NACA ACR No. L5F27


tH-HHI-H-r-H7


-- :- ^ ^ -- -- CONFIDENTIAL --- .-;-.- .-. -- -- 1 ^:4

-.-|, '.- ._
A E 1--Tt




I contour



-4 --

LA. 7






v I I







---lo
.--


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










--6--
T i iJ



-T s -S -- ------.- s-- ----- --.
-" -.0

1- ;.. ;, .i_',,- -.


J,


_- _. .- -,. .:.-








-- ---*----- : ', ,-1






-5








_.- CONF IDENTIAL *--
I' I I ,.


a dog


sectio glel i attck I0 l I


CO


(b) R = 9 x 106.
Figure 4 .- Concluded.


F -T


NATIONAL ADVISORY
NMMITTE F AERONAUTICS


-_-4-


, ,


ff


*1 1 1 lt + :-- 1 1 1 i r


i 2 I I 3 I l II I
IL I SuetIon angle of attack.


Fig. 4b






NACA ACR No. L5F27


Fig. 5a


7 + .: 1- 'E ^ g |i ^^' ,i 1 3L
--.. .. zrtfI4I qrr.r.r -,.1, r .t -F ....

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ail n o u a l contouroa oi s on
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r .. ..n t i o" a- -l e o f ata- r d e


t II = 1 x 10 .
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i t T
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|||r + 441 i -',,+r 4
















I.. s CON1ID7 NTId -1( .






Tests, TDT 84b7 and 848.







NACA ACR No. L5F27


L4 f ;.l I r..


.i ,ll
VT4


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NATIOUAu. AVISOl -


^;,: V! r :g^ C N IDE A>L..^ ^ R ^ -' *''': **<>*.- *
^^^-it^^NFI DE.^l^rj^ j -


geotiLm angle of attack, ao


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L


deg Fr


::mt: tmt*1 4: h L# 1 i l4 I I-7lM11V -111---fI


(b) R = 9 x 106.
Figure 5 .- Conoluded.


+-b


Fig. 5b


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Tf'-T. Il' I J'








.NACA ACR No. L5F27





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NACA ACR No. L5F27


-4 ,

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NACA ACP No. L5P27


Fig. 7


L. i --, -.
-4 i 1 ,. L- '--" LI.L _L.. A. -- --7

S -- True contour
CONFIDENTIL Standard L.E. roughness
S CONFIDENTIAL -

A





4T_!4 .. .-.... -...... a.. -L 14 .



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Pil r .... --. .--sr4 ... -



!(- .( o
I.- --



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15,-- 1-- -- .- 5 1-"
II. I















CONFIDEXTIA f. '____ NATIONAL ADVISORY
T- CONFDEN TIAL .-_ -COMNITTFE FOR AEEONAUTICS
__.4I.-.-_. ,- -j I------ ----. :-- -- ----l.--j. .------- -J--.
-.. -p o ,! 1 1, -- .



e -' .- r-.--



I :r,- -- I


-,, -u --20 -m:


CONFIDENTIAL ... NATION AOWS~nY
I' .. 7: O MT F FOR AEM_ "- t


- t iu- --


.-p f: -


: -22 Section angle of attack, ao dog i. ,-,, ,
T-' -I i-- :I--i 1 -f F T 7I


Figure 7.- Lift characteristics of an NACA 651-210 airfoil section
equipped with a sealed-gap 0.20c plain aileron of true airfoil
contour. Standard leading-edge roughness; R = 9 x 106; test,
TT 869.








NACA ACR No. L5F27


Fig. 8


I :4f.
i---- V F = I I il I j-- .


4 CONFIDENTIAL
1 --- [


64..i L 44,'44g:- -.l.


True contour
Standard L.r. roughness

m ::1*l-it-t-^Tt h-I


r.-FjL-. r:F r I t r :1 1-


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rM


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15

20[
C04FIDENTIAL -
^-AlJ- !-,w-


LLC CHChI~


---I-I Section angle of attack, a deg
7 I I I l l


-NATIOINAL ADVISORY
COMMITTEE FOR AEROMAUTICS .


Figure 8.- Hinge-moment characteristics of a sealed-gap 0.20c plain aileron of true
airfoil contour on an IACA 651-210 airfoil section having standard leading-edge
roughneea. R = 9 x 106; test, TDT 868.


^^i:^^:.-


... I. 1H


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r


iji~


:-.." L *- ]-A. *---I ;:-


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I







NACA ACR No. L5F27


TTrVr IIV:H L I I _--Il __I-t'tt-


Th7T-


L 7>- 7>


I CONFIDENTIAL


iTiK
| f L-J| __J ---I___ --
7:^ =^: ? I-


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-1 A4-4- t-


SSection angle of attack, a deg
I CONFIDTI-AL -T-
j_ CONFIDENTIAL | [ I .


True contour
Standard L.Z. roughness





-- -- -- 20
" -- -- -ba I



--i -i
15
10


o
i 0

-5^


COMMITTEE FOR AERONAUTICS
-1 -- .


:'l :


Figure 9.- Pressure difference across the gap seal of a 0.20c plain aileron of true
airfoil contour on an NACA 651-210 airfoil section having standard leading-edge
roughness. R = 9 x 106; test, 7DT 869.


I .




!14
cr

iI

- s
-
- ,
c
{"



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Fig. 9


Tr ,u- i i. ; .- .T." -


II II I I I


--- I--- --- i .; i ; ------ I I I -4--


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i


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t


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1







NACA ACR No. L5F27


-If41J241L1211121LTJTFT7I2IfII lI 111 TI PI


TIAL:


-- -11-- --^ ^ -^-- V -

(d g)
0

15
20

T-17 xI--- -L
o ^ / ^ 'f- / ^ ^' L.
-- -- ^ c --:"^^ -' -'-3 --! f- f -**- -St


-o~ I I }.l
- ----- ------- t
_.__-.._ ^: VA Y^ d .{yy ^- ^


^^^^^^lei


4-^


WSA i J -it tS


Os

deg)1-


-15


.U- I4 I 1 I I t k! % -t r it


iLk~


4s


CONFIDENTIAL


) I I I 1


\u,~i


SSection angle of attack, a dsg

(a) Rt = 1 x 106


PtL re 10.- LLft and pitching-moment characteristics of an NACA 651-210 airfoil section
equipped with a sealed-gap 0.20c plain alleron with straight sides. Tests, TDT 854, 861.


?Th

0
-u
r

7
U
-a*
a"



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-a
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0

oi




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- -


















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NATIONAL ADVISORY i
COMMITTEE FOR AUENAUTICS
WSB
I t --


Fig. 10a







NACA ACR No. L5F27
Fig. 10b


I. : JFiOENTIAL v r _







0







-0 T5
r jr






iii 'ti-Ma j I.T i, 'M)v Till- iti
ST. "

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3 F, !_:
Lts)i[T~


-ao


-15




10

1F0
1-5
20


L 'ADVipaRY
um radurMTIC


11


oI


t- ;I. I ; ; i 1.-- ta ni


Section angle of attack, on a deg

(b) R = x 106.
Figure 10 .- Concluded.


f.


T..: li IV


IaJY 'Y L


r


j- l,': Jrm .


ini' Ti 'rngr.irnri" i ni jiTiilL ** r-s-


f


-4_ I; 4 1 9 1 1 1 1 .. L I I I. .. ..


- '. .- 1 .1 1 1 F i I I


I YI4 ;i


~~-tf~fff~ETTf trf-


.3







NACA ACR No. L5F27


Fig. lla


a~r d*.Ia


i 20


Figure 11.- Klnge-mament characterstlcs of a sealed-S-p 0.200 plain aileron with atraiht
aides on an NACA 65i-210 airrfol section. T.ata, IDT 852 and 860.


i







NACA ACR No. L5F27 Fig. llb


-_. -6 _L4 1JL __-L1. _L U..'
Section angle of attack, ao dog
=7-77T 7Y-T= L LL


Straight aided
4 I: .- ja I-C f I" I I


Lb) H = 9 x 106.
Figure 11.- Concluded.


+


...


I








NACA ACR No. L5F27


--I-- -- -- -- -- ---- -- -- :--. -I

.- T --
4 I




CONFIDENTIAL
. 1 I u Straight aided


T

S---3----
- 4-l -!-1


--



-- ---




L. ---





__ .__ .___ _















CONFIDE ITIAL C E FOR AMKNALTIC5
Jr
(a) R-= I--+-



---_

I I



~_ ._ -_.-
I NATIONAL ADVISORY
C O N FIDE N T IA L r-- /
_I i i i i--
, Section angii of aot,,ri, a d LI_, ..




(a) R = I < 106.


FpBure 12.- Pressulre difference across the gap seal of a 0.20c plain allercn with e~raight
aides on an IACA 651-210 airfoll section. Test, TDT d35.


I F


15

10
ar

10-
5

0-

-5-

-10-


I 'l l i i i i


I I 1 1 --


Fig. 12a







NACA ACR No. L5F27


'; 4,' Mill r;, -
_, t.,
I liSR d] "g "|l ii||.'lg t:lr..lg : l|||g

g l ; Sl + ^ S' f '-:: i .77..':1'- ; :'"


Ti .i"t 11 T-i 4 >
t-i ; '4 --, i ". .





V ir4" .t S -: 3 i .:',tralght -id -d




ril
trr T1

,:: [.': P.w__ ._ n-. _': ,-... ss i
2_- u -r :ti tt,. ',t(;ded






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-' ,114g !z- (d :





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p 110
." ..... .
,, .I-,^ i

.I I' |,p^^s=^ ^^p -^^^ -
--17







ILI


. t i ti I I 12


Section angle of attack, ao dog


i--mT I- I .0

(b) R =9 106.
Figure 12.- Concluded.


tI 2btt


- EhuliLILli


~iN'itl'VKH~Y lf;tliL Vr


ur~llllr~
--I--c-L


I


- I


.1 1 1 + -"


*-* .


DIFN ENTIAL


ii f: IC. f~ ~:


Fi g-. 12b






NACA ACR No. L5F27


4- -- -J -- -
14i7.' +
l Straight sided
Standard L.t. roughness






4 -





1=75
2 0...
:--... .. .:^ : ^ f; :11# f-^ ^ ^ S ..^ :::!! :::-: ^ S *

















.'CONFIDENTIAL N|- NATIONAL ADVISORY
...CO ITTEE F.R. AE.AUTI.
Cal 0 z^sI ls ^^^^li^
g |! |+ .....1....|.^^ ^ i il
IS:|:U |"i ^ ^ ^ ii~ ^lg lT i ;! ^ ^ :!!!4

Ill 15| I 1li' 'll
ti|t. cl -H~ |il 1l|
1 II0
lii~~~a...... ...g i ^^ ^ ^ ^
%4i g 'g ig5||:tg ^ c*"T"",n*Tt'


SSection angle of attack, ao dog
-. :-. A- ga~B jE ~ iItJ~f~f~TIl!^ -.


Figure 15.-
equipped
Standard


aE


Lift characteristics of an NACA 651-210 airfoil section
with a sealed-gap 0.20c plain aileron with straight sides.
leading-edge roughness; R = 9 x 106; test, 1DT 864.


rri^


Fig. 13








NACA ACR No. L5F27


Fig. 14


Section angle of attack, ac dog


Figure 1l.- lnge-mament oharaoteristica of a sealed-gap 0.20c plain alleron with
straight ldes aon n NACA 651-210 airfoil asecton having standard leading-edge
roughnem R = 9 x 10 ; tent, DT 863.







NACA ACR No. L5F27


Fig. 15


-44





B ^ ^ :. i. L ........-......


Id l :. 1 --
S"I "



,+ 1 ',: : Ii. '*'
pS '" traight aided
:'_'_ CONFIDENTIAL j 3tandatd L.Z. rouguema




'- g .a ,d ed I- --l ^ Es
-i'.J Standard ..B. rougbg




















5 ,,--
,1

., P_ !I.- r. -

















,Ii; NATIONAL ADVISORY
m aCONNInU rm *ENwrIS,
Lr I ,f "-



,T 1


III I L I eI t .1 fItSection angle of attack, a deg
WFTFTTTYVF]II AIIL l1T TTlIr~ I -T,\: n I-r


r1~I7I171~VTVV1~V I


T I I I I I II L.LLL,,M


S '.
....I J ~.I, _J,, 3. .


Figure 15.- Pressure difference across the gap seal of a 0.20c plain aileron with
straight sides on an NACA 651-210 airfoil section having standard leading-edge
roughness. R = 9 x 106; test, TM 864.


I I







NACA ACR No. L5F27
Fig. 16a


I al


t 1t:i


ia J*- I 1 r T. -T. i .i I rtn


- Trrt.-tl-t--a`
4m4J~4If4U'~4~.l1ItJ


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(an~


0
5
10
2I


Bevelad


'L2vLh2&t ., -f-p.Ar itL ,i r.flttmflt


S.'4


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u ... ..


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- (dsgi
97--1;
C;


Il I IA TIOL I
|sa -I | -|| |

i-I : JA: .



4 .





7'-L -r 5 ,I
4-"0t l -WmImIS


i-l+l- -i.. t'[i- *ij


e teotlon angle of attack, ao deeog 1. l2'


(a) = 1 x 10.


Figure 16.- Lift and pitching-aomet characteraitics of an HACA 651-210 airfoll equipped
-with a sealed-gap 0.20o plain aileron with beveled trailing edge. iots, sD 858, 859.


MiLA4A4


Wtitt Iro "T'-E


I ::L4111, r -
f3 ,.4*''- CONFIDENTIAL


i-z jm i LJ I


'SFt~i! fa15f


.~L'"~'`L":' I~ 'YII~;IIY~:I~~L~ ii~-T~~1-711 Lill---il ; --1- ;-~mT-


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M 1


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MPR P;.. l. m m r~ nr-- r -


II


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LNLi


II


i:;1'91::~f~lfl Pf~P~i~Wf~T~I~1 ir(S~t ,, ~Y~L~


-., _.- ... 1 --







NACA ACR No. L5F27


7.f9if.;4-1Wl1ThiiT T14TWFJ~k;FZ-r'--'1 W rM-- ----


r 4'r 'i l ." "l- l .*L ,-'ru "i .: '- "rrj.x it-' t *-, t,: nt. l-T7-


ziCaiLu STV TiiL~ fliWAi LITt


L 1 .


4tt li- It'i '7


Beveld
tIA1%ttLP^Jj LI


.1.-
ao
-|| ;4L-' (dog
^^-'h^S iN'^ ^S Li
^~~~~~~~~2 Ljg^l|iAc||t~l


I S ifc^*''^1', 7*;*' T f w ^rpi* V *' i *~i n7

1+ --'tME
1-- -.2 : il_ :


4.. lit t !i|

| 11171151


I -7-,1.-. ._. P -3


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7 -T i




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-LT I

.-AA v


deo)
-20
-15
-10
-5
0
5
10
15
20
-F


1T7 .1J17V I V I 1 i, t I I.1:3IlIII-.lIfTll IAI II


_NATIONAt LYSOBY
M'- CONFIDENTIAL J CDo l n tm AEmuIMucs

Section angle of attack, a0 dog

(b) 3 = 9 x 106.
Figure 16 .- Concluded.


X:71 i x
, 4 I :
r7-V7


4T


fl~W Iri;nf~F:Trr


4


fi
^r 5



-a
:* 4 a

rr]
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Li

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.8


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..l..-.*sl^f-r^..rTtt.n^' i. *

;L.ii.'L:


T


P-H-j


F z n : Tr-


Fig. 16b







NACA ACR No. t5F27
Fig. 17a


r .1 ..'1


:4rflT~fl7Vr7-T-rI t 1


NTIAL t


t--. I'


=01 Hl'. 17. T


*i f ~ In f -J- *I


Beveled


--'- A-' .-_~-,'-. i i *T : .. '-- ---i. '._.' -- -4. rx t- *' I '-1 ~ --I- i-i-_- -


trJr --~t- 1 rm~'-T-p~r< '1~ -~zErI--~J 11lr,


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t -:-t --- t: .. < ; -


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|g g _-Ig :- ::
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1" 'A -T 1 '

J.- : 1 i! .4411" 0


_A- .... ... .....



.. X..


P '----I I. .:- J


... I. ....- -


-- W -1


!a-1" 14TrrKi-F


Kill


IF I! 1 1 I .


.. ON -D TIL I
; .A CONFIDiNTIAL- -- ---- --- --


H-- : ^--
NATIONA
COMMITTEE I


-L,


(deg) L I
-20


S10


S20

. ADVISORY
M LOrUIUTICS


FIT ~ ~ ~~A1: J -.ii..l


(a) B = 1 106.

PFgure 17.- Hinge-momnet characteristics of a sealed-gap 0.20c plain alleron with
beveled trailing edge on an NACA 651-210 airfoll section. Tbst, ODT 862.


R., HI.t


.. -l:l. :l i- .. .v a .. -I -I -


h.N ^_1.- : A;P@ 1H t


33~iE


fi-^N^


7 -1-
- -inr
-* i ~!n:-i


"-4


" :K.


CoNFII


.-_ 44._i4- -


'~"'L:~l I 1-I- I~-~tl-~~ ~-!(Y! TYI-l I I I--r I~ I.1 ~ .I -L.1. ii~-_ittii~-~t(


-- I'~-'r I 'F'l::- I.* 1~CII I 1 I I ; I I~ I I I I 1~_1. I_ I I I I ~L-I I I


: 4u *.. :. -T t+1 -W I U I I I IN! I i I-r- -r


B .-, I I I ] -


P! ., r


-{**.-. I--'


m -1.


,t -it;:


k' ".-\t


-


15


I ,


-11


I I


-i-t


,,,,,..,


I I I l l


I.. I. -.


S-~I Section angle of attack, a dog
L^N IFT'-f-- I 4 I 1 l 1. .1 J I


t~;L~7t~-t~-


'1- 'HI.







NACA ACR No. L5F27


(b) R = 9 x 106.
Figure 17.- Concluded.


Fig. 17b







NACA ACR No. L5F27


Fig. 18a


tfl~lt~j:~tW '- -~ ::*; YJ tint: f' h$43EF'Tf~:~Hf*LE!Iit~th tL.t'I lllWA4Ed~f~ti~tA'Y4WIPfhifl.TWInifl7


ta it


"f4Lq ,fl ,2 ... ...t.. -.....


4- J.- 2- j "l t! i --i .. '' .44'4i-T- i a& ;I %4
4 ~ .
I-!.. II ~ 'N


*. u 1. .-il tt-'tt~AffiiftfAl-~irLuC*J-i-4-" ',


t tt- t~'~ft~ht34~htr -L~li1,-f P4It'I- LJ'4I4JI


.ir:- i 4lu m-nwi-ir-r,U itt tnt-~ tnftutLi ttt i -I iZ I 'i.a;t ~t L. Irt 1 1 1 IAF-il4


rit ItIt r-,
:;:j 1.4.:M4 L4


S-I--- -V iF I
l: : :-L : :

CONFIDENTIAL


lt I ": 'r k
,i fl-u 1 .fi1r 4i ,f :evlr



A- (dog


,m;il i 11! .; i1 -' i -
S. W!20


S L .1 | |.|||i || !|, ... |
I4 l41 7I17 I


J-r
.m 5
1P 5 -" i :-+" '

I i sit
i i t II


4T u-
| r --B -- "|||| '-4'
-- : .




I -V -

..._. : 7. .


4ti1I~4{'ii I I ~liA


-1i -8I 1


Secttan angle


of attack s dog


COMITTcEt r .u.v.I


(a) = 1 = 10

Pigire I8.- Pressaur diferemo sroas the gap leal of a 0.200 plain aileron with
beeled trallag edge a an A CA 65-210 airfoil section. Test, DT 859.


I I
1-17,


pM 1 i. : -[.
jt
I ZIE -LLliI~I


rnnrl .I- !.u; rhmtt +H(t.l~t.+tt: ,. rte~ iil'r- ~~(;t;l~lili-rrifri7:t~i~~FFr~m


"nmn


^ :i 'r R. 1-,1
l ,i 1 : ..


''


at;3;F~


~~ r .. C~~-~-- WCYY~LYY~Li ............ ...l~~l


1I ,i-;.M :'- .i -LI it-' n' tt1"1 *E+V


7. ..['i-'y +'.,i ,.i ;'i A M'; l"iu l.i1


Ii i {.i 1 .iJ ] l. 'i" '


I 4 T i -- io


I i !


i i







NACA ACR No. L5F27


I4 "ij :'i. .E ..*- uT .
1lf' ^+r iiig-l-
1- I-.


- .; I* A7tr1' 4:!q: t, it jlf-rt,- j f r flj fgj


M11


m i LtKfj,

E4rsptf2,


:tti ~


smm-^i


Idt-IW#


tIt'f'-i4t+4H4+


~4j~u~ 4A.4Jflr'4t4E4tl4


ii ,tf,;- -41


if.t+ .,.%1 ,.F1A L IT


Beveled


i ,I T4 ..::-i .^l '-


." CONFIDENTIAL 1 i

S(dg)



M10



15





W"I -- -5,
. .!T





















et angle of attack
*l E __--___.____..____ __ -10






.I I
.--.:-"J .i- il7-


i -.15] ., ..
; 4.... L1'[ '- ---





-LI: 7 I M O -JU I



I i! -T j'g.


I t ..I 1 I l. ,f ,,


,w Rt ,.


if -F'4WUiHth4UFIWfHEIW-S2EV


- Im'J.I a


*jLfUi1*1 J I I -I t I* .[T* tf *U-
(b) R = 9 x 106.
Figure 18 .- Concluded.


I. .'4


: i


99M L
-L.
i'F~CtFR.1;:;f~;JAEf~l
liU!


-Tl
*.**-wf


,, '.:1


i V M P


*:"- T!-i i.ff- r tri.Ta fis


""'


`"'"'"'"'


-1


Fig. 18b







NACA ACR No. L5F27 Fig. 19


TflltLtL4ittL~4 uVi


Vt 44


CONFIDENTIAL
i


2d'~ J21 HIlT 212221W


Beveled
Standard L.K. roughnes


44





0 7 20














f:OFDETA A
-10






CONKITTEE FOR AEMUTIKS


Section angle of attack, o deg

N coNFIDENT IAL.

Figure 19.- Lift characteristics of an NACA 651-210 airfoil section
equipped with a sealed-gap 0.0Z plain aileron with beveled trail-
ing edge. Standard leading-edge rougbhness; R = 9 x 106; test,
%)DT 866.


I_


I


YYLYYYY~ I I I I~YLLY IYLL YILYYL-


R^-li


~- ---


"~ '""' '"~'


ifflg


r-Tr


4t


f~tMT _T


&titi


r" it


it, I M i.11111111.1i.M li' 1


Si '- F 1 i- I


T~-~E;f~ii







" NACA ACR No. L5F27 Fig. 20


Section angle of attack, no dog NATIONAL ADVWS6 -.


Figure 20.- Hinge-moment characteristics of a sealed-gap 0.20c plain aileron with
beveled trailing edge on an NACA 651-210 airfoil section having standard leading-
edge roughneas. R = 9 x 106; test, IDT 865.






NACA ACR No. L5F27 Fig. 21

St :Fig 2







F '1-t, '.i j i ~ r
|^,7 [ Beveled
S standard L.E. roughneaa


hi i-C L ---- a UCONFIDENTIAL-- --


SI- NFIA-L'- -- -
a N ad L.. r oughnes.

aeylP~tikf^^^^^'E~rf~3li.7;::illl~ta'-- i l? !. *.- _- i





C NF IDEN l S33




|j TL aAL-[it- ^- 1
'I i .,. -P F, 4. A 4 7, I
I I .
















L, -. I CONFIDENTIAL_
1 .. --

:I.~Eil~.. I~~t~ '1'i It. I' li'. t I I i 1 I : I I I ccmrr~rmr~aOrTly
WITEEINAWAUIC
t Lll.p: 4-' LE 'ItDFN ~1 t-:CNF~NTA
T .......


'4- ; .- -4 i i- "'.-F. 4 '-F -


Il -" I L


m.Lt


- Seotlon angle of attack, o deg
-- I I t- i- -T T T I I


Figure 21.- Presaunr difference across the gap meal of a 0.20c plain aileron with
beveled trailing e4ge on an IACA 651-210 airfoil section having standard leading-
edge roughime R = 9 x 1061 tet. m)T 866.


rtltt~tl-








NACA ACR No. L5F27


Fig. 22a


Aileron oeflection, 6a deg

(a) 'tue-contour alleron.
Figure 22.- VariatLon of aerodynamic chbrfcterlstce irth alleron
election at a cor.stant section Lift coefi clent of 0.0O for
an NACA 651-210 airfoll section equsppea wlrh three Lnterchange-
able saeled-gap 0.20c plain ailerons of different contour.







NACA ACR No. L5F27


CONFIDENTIAL
SR Airfoil surface
--- 9 x 106 auooth
----- smooth
8 -- ---9 standard L.E. roughness


StrgUht aldae


-----= ^ ^ = --- o






1.2
.8 -- -- -------- -.






p 8


















-1.2
*I -- -- -- -- -- -- -7 -- f -- ---- -- .



_ X s __ __ ^ __ L "_ __ __ _


S-.
'I




0
i
o

u -
lo

I "


1 1. .1 I 1_ 1 -1 N -.,2,


-20


-16 -12


CONFIDE TIA
CONFIDENTIAL


-4 0 4
Aileron aeflection, 0, dog

(b) Strsagt-gided saleron.
Figure 22.- Continued.


S -r--- -.a,









2 NATIONAL ADVISOY
COMNITTIE IO AEIMAMIICS


I I I I I I


8 12 16 20


Fig. 22b


12


08




a




41





.12


2








NACA ACR No. L5F27


-4 0 4
Allerorn efiectlon, 6a deg

(c) Beveled aileron.
Figure 22.- Concluded.


Fig. 22c























.16



.12



.08
a





.01 .







.0



.i i
.-1





.12
.s
-.








NACA ACR No. L5F27


Fig. 23a,b


Ano/AGa































ACH

Aao/ABa


.01---------------- ^-------------
.01





















(a) Smooth airfoil.

.01
"_12 -- 1,--


..01 --^^ ---__--------














.00







NATIONAL ADVISORY
CONNITTUE FW AMMt*IC5
.02 --
0
.01--




CND NATION L ADISOY
.02
.0 -- -r"- -


CONFIDENTIAL
* --


Aileron

- True-contour


-- Beveled


Aileron

- True-contour
- Straight-sided
- Beveled


-4 d
Aso deg


(b) Airfoil with standard leading-edge roughneee.



Pigure 23.- Variation of the hinge-moment parameter AcHT with equivalent change In


action angle of attaok required to maintain a constant section lift coefficient of
0.20 for deflection of sealed-gap 0.20c pain ailerons of different contour on an
NACA 651-210 airfoil section. R = 9 x 10.


CONFIDENTIAL

-- __ __ __ __ __ ,,_ 4,


IAK/kA


. Ytralant-allls~


-


-2


-


4 0 12









NACA ACR No. L5F27









.ua contour 6


True contour


Fig. 24a,b







0b Cb
.5531 0.396


Straight aided


Beveled


ANo

































,"O/Aa


.0o
CONFIDENTIAL


.02



.01

.0 -- ---- -- -- -- -- -- --





-.01



-.02




-.03
-.02 -- ------------------------




"-12 -8 .4 o 12
Aao dog

(a) smooth airfoil.

.05



.02 -



.01--



-------
P-




-.01



-.01 -----
NATIONAL ADVISORY
-.02 COMMITTEE FM AEM"lITICS


CONFIDENTIAL
-.03 -8 0 4 8 12
-12 -8 -14 0 4 8 12


Aileran

fe-con tour
Straight-sided
Beveled





























Aileron

Bie-contour
SStraight-sided
Beveled


oAn deg

(b) Airfoil with standard leading-edge roughness,


Figure 21.- Variation of the hinge-moment parameter T with equivalent change
Aco/Asa
In section angle of attack required to maintain a constant section lift coefficient
of 0.20 for deflection of sealed 0.20c Internally balanced ailerons of different
contours on an NACA 651-210 airfoil section. R = 9 x 106.







NACA ACR No. L5F27 Figs. 25,26
Fl gs. 25, 26


CONFIDENTIAL




2
2 ----------------------






1
2a-- ----- ----- -- -- -- -




I --- ---- ---- -A----




1
Aileron
~r True-contour
traight-sided
Beveled
2 -- -......- -


-12
-12


CONFIDENTIAL


NITlU0NAL ADV5iRU
COMMITTEE FOR AERONAUTICS


-8 -4 0 I 8
Increment In section angle of attack, AcO aeg


Figure 25.- Variation of increment of section pitchlng-moment coefficient of an
NACA 651-210 airfoil section with equivalent change in section angle of attack
required to maintain a constant section lift coefficient of 0.20 for deflection
of the three sealed-gap 0.20c plain alleroni of different contour. R = 9 a 0o6.


:- 'l' MI I I----T -NF- EN T
IT ",/ l', l i I CONFIDENTIAL, ----
i1FT-l -]7-


-- Aileron
S True-contour
--- Straight-sided
O 0 Beveled


'T-FF


I11 It'I I'll11 1 IT


S-- CONFIDENTIAL ----
; I I I I I l I l] I I I_ !


NATIONAL ADVISORY
COMMITTEE FOM AERONAUTICS


Section 14 angle o attac, l L_ d
I SI SBection angle of attack, a deg |-
'- .- -I I I- I --


Figure 26.- Effect of aileron contour on the section profile-drag coefficient
of a. NAGA 651-210 airfoil section equipped with sealed-gap 0.20c plain
allerons. 68 = 00 ; R = 9 x 106.


I.



Fr


0


4
:0

Q


V
L a

L .

.i
-'a
S0
, ,0


* o
w4
-s

-5.
Lu

. o
- 4
0

-.


'~'''''''


C"'


_p~


1 t


77T


















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




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