Document
ACR Bo. L5F2
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
\ -() ORIGINALLY ISSUED
December 1945 aa
Advance Confidential Report L5F27 TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF
o .20-Anm:>n.-CHORD PLAIN AILERONS OF Dll'F.ERE1fl'
CONTOUR ON AB NACA 651 -210 AIRFO IL SECTION :By William J. Underwood, Albert L. Braslow, and Jones F. Cahill Langley Memor1al Aeronautical Laboratory Langley F1eld, Va.
PROPERTY OF 1fT P ROPU LSION LABO ~ ~ _ CA U F ORHI~ I NS TIT UTE OF TECMIIDIDSI - WASHINGTON 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 pre- viously held under a security status but are now unclassified. SOIDe of these reports were not tech- nically edited. All have been reproduced without change in order to expedite general distribution.
L - 151
NACA ACR No . L5?27
1\P.TIOl'JAL ADVISORY COk)'ITT.EE FOR AERONAFTICS
O . 20 - AIRFOIL - CHO:,D PLA n·. AIULRO:;:~S OF DJ.:FF'ZRENT
CONTOUR ON AN NACA 651-210 AIRFOIL SECTIO~ By WilliaY:1 J . Uncer'Nooo , j,1tert L. Bras 10""' and Jones F . CaLill All. in v'S s ti ga ti on WE-S ··l!aa.e of' three interchangeable sealad - gap O.20 - airfol1 -ch~r d plain ailerons of diffe~en t co~tour on the NACA 65,-210 airfoil sectio~. The three aileron contours test~ci ,ere the true a:i..rfoil contour, straight sides, and a bevele::3 tl·8.-Lling edge . 'The effects of aileron cor.tour on tl -: e section aerodyna::nic cnaract"lr- istics of the airfoil 8r!d aileron are preseLlted herein .
The r :' sul ts of the tests inc . lcated th'3."C thickening or beveling the ailero ... trailing ed.ge by the amount iDvestjgnt e d v'ould decrease the a:'lsron effectiveness, the rate of change of s e ction l if t coef1ici~nt with section angle of attack , and the -:-eaxhnum section lift co effic:tent; woulcl increase90si tl vely he rate of change of section hinge - roment coeffici~nt with ~ th sec ion angle of attac1.c and a11eron r'leflsction; v'70uld shift t -~ lE .
a8rodynalPic cent3r forwa rd; and woulr'l causa no signi;:' i - cant c hange in t~e secti on profile -cra g c8eff'icl'nt with aileron neutral or in the incre ~en t of s e ction pitching- moment coefficient indu c ed by aileron c.ei13c ion at constant lift . The b'3.1ar.clng: Eoctlon ':)i' the ::,-~.L,r"n a:'1d the 108-3.1.11..9.il-3ro:: effectiver:es3 caused b; bev71iq~ t~1e tra i ling adze Vie ~-3 2'Cv~ntua tlSo by U"_'3 application of standard .. leadin g - e-c..ge rough...'1e.ss to th::; 8.irf;:,il. ':'he computed characteristics of the :;lrree - -s-<,;ale..d int&T'l-:ally balance-c1 .--e.ilerons , bas ed on the data for t'18 hinge- moment and seal - uressure - diff ' rence ~oefficients of plain .. al~eNms, showed an a '9p reciable effect of ailer on contour on the hinge Y!:oments a t the larger aileron deflec - I tions even tho.ugh . all thre-e .a·i13rons .... were Jo Yrputed to hav e the ~ s1mie h' nge-moTIlErl t slope at small aileron -deflec - tions .
j
2 CO l'Jr.'I DZI "T I !-.L NASA A CR No . L5F27 IN'IrtODTTCTION ~h6 use of thin airfoil s3ctions to de l Gy the effec t s of cor ilp ress~ bi l i ty on tr.e wings of modern hie-h - Derf'orm8.ncG airp l anes has emphasized the need fo~ ~ata on the aero - dynami c charactl3ristics of ailerons on thin [tirfoi l s . The effects of 8.ileron contour on tll2 aerodynaJ11ic c:--la r acter - istic3 of a51erons have bsen Sh01TI prpviously by invssti - gations of 9 li :;-.1 t8d nurrb::r of airfo." Is equipped v:i th control surfacss. Slnce very littl e section aerodynami c data are a v ailab.8 for ailerons on thin NACA 6 - ser1 e s airfoils , tests were made o~.' an Fic.CA 651 - 210 airfoi l equipped 1,'Vi th three interchangeable sea19d - S8.~9 0 . 20 - 8.irf01 1 - chord plain ailerons of different contour .
The inves t igation VIas lTIade 1n the Langley tv:o - dimen sional 1 01N - turbulenc'3 pres sm:·e tur.De l. The three ailerons tpsted differ only in contour and are designated herein 8.S true - contr:mr , straiE.ht~sided, and o'3veled ailerons . The hinge rrorrents a~.1j effectiveness of the ai l eron and the pi t ching - 'n0men t and :)1'0£'1 Ie - d r ag chal' - a ct eristics of the airfoil were deterrrL1.ned . 'I' 8 sts wore mc;.de wi th the airfoil s 8'f [3-, 8 Bcrod T n8.! :.. ic a lly smooth and vvi t h stBnd8.rd roughn;ss a·")pli~d t.o the lea.ing I3dge of the ai r foil . The differentia l nressures across the ai l e ron s:;a1 were obtaim ed for use in cal c \.l l at1ng the hinge - ~omen t characteristics cf ailerons having any amoun t of sea l ed :i.nte-.C' na l 8alance .
The coeffi~i en ts ar:d ::: '2T!J·.b ols uS'3d herein are as fo l lo NS :
I ~ \
airfoi l section l ift ~oeff~8ient
\ qo~ )
airfoi l section profile - dre.g coef1'i lent ( \qd~ 0
o / c airfol l ··section pitchln; - n·,omsnt coefficient abou t mc / 4 \ quarter-cnor ri !-,oin t ( m 2·\
.qoc J
l
NACA ACE No . L5F27
seal - pressure - difference coefficient ; positive 1phen pressnre b9low se , al :] .. s greater than pressure above sea l aileron section hinge - ~owent coefficient based
on aileron cLord ( --F~ )
\ qoC a coefficient based where aIrfoil profile drs.f ::'9 r u.r.i.. t span 8i rfoi 1 --;i tCh~ .E g :110r: ent per uni t sp n aileron hing9 rome~t par unit span; positive h wren CJ.~12ror t3nc<s to defloct d v!l1ward chord of airfoil with at~eron neutral c cll.ord of ailerorl b ehi nd h5n.s3 8xi s
free - s tre Grt d yno.m.! G pre s S'J . re (~r:;1 0 ~
v o frsc - strear density airfoil section an31e of attack, d~gr2es aileron dAf19ction ~i h rcsp3ct to clrfoil, dcgrJes; po~itiv9 'h3~ tr2~:ing efge 1s C ,-;1" 13 C t0d down", ... ar'd
r
C OrFI DEI~TI .AL NLCA ACR No . L5 F27
CJ .i n ailE'r'o!'l 3'3ction eL"":c t.t v er.3SS ra r 'J.m-:- t e r (rJt.'1.o of :'ncre- .ert of airfoil s-_ction ar:; 1 0 ci' qtt2.C~; to j.ncrem · :mt of t.dL;ron deflection req~lr9d to rraintGin con- 2tsnt lift cos~ficlent)
~ACA ACP No . L5F27 CONFI~2~~TI AL
total 1n s t eady roll n rssponse 9aramete r (reference 1) inC.i.'ement in aileron section hinge - norr.ent coef - f~_cient due to a.!_lerol1 (leflect10n &t a const&n t section angle of attack inc :'e 11:8 n t of' ai ~eron se c tj on ~l:.r.ge - I'lOn'ent coe f - flcient due to cheng0 in section angle of atta ~ ~ at constant aileron deflection increment of t')t;D l a:Ll'3ron s:?~t::'on hinge - n:orrsnt coeff!cient in sts &6y roll The subscriDts to p~rtial d0ri vati ves denote t.he v'1riaoles h3ld constant v. hen th8 9£:.rtial 6:;ri vati ves were tal'en . ';he dEri vati V3S FeT' -, meas'll'ed '1t zero angle of attack and ze~o aileron 1ef19c~icn .
ThA modpl had a 2h - inc~ chord. and a 35 . 5 - inch span B1l<"l was constructed of leiyinated J18r: cgany wi th the exc8:;'i - t ion of the inter~h8:1g '3ab le ailerons , ",:hich -'Jere cor.st-"ucted of so l id dural (f~[ . 1) . Ordinates of the NACA 6S, - ~Lu Air - foil section '1re given in table I .
T:1'3 t1-}rp8 aIleron sl-1~:)es tes-:;"'c. a:::>e shotrn:;. 1::1 fisuY'''',2 ancl conc:ist of the true airfoil cO~ ·l.tO·L ~ , st::,"sight ~)J C18S, and a bevelsd trailing eege . 1te 0rdin~tes 0f t~~ ~:::>~e
C011tOu:' r::i18r0n Nere t~Je sa::1e as t~.e JrrJir.~l t~s gi veL i::1
tabls I for t~e trEilin..::: - e:it;e ~art of thp FACA 651 - 210 air - foil se,~tion . Th~ con ours 01 th 'J str'3.i[.ht- - s~_ded-ar:d beveled b.ilerors '..~rJr8 :'Jr""3d b str<:ig:~t liYl'-'s as sbown J
in figu-e 2 . A r~jbar seal pr~ ~sc~ at t~3 zap at the
nose of the aileron.
F8r the t e st: of the s~0oth airfoil, the ~odel was
flEish.:3d t}.i th 10 . L,oo cclru·Jr ·m dU'TI )aper to prOGU88 aero-
~yn&rrically smooth surfaces. For tLe tests of the air - foi.l with sts.ncard 1e8.dlrig - edC:b ronghness , the rrLodel C () NFl D'!: !'\:Tl A T J
6 GO?Jli'I D5NTI AL
NACA AGR ~o . L5F27 surfaces were the sa me as those of tLe smooth airfoil ex.ce~,t that O. OIl - inch c arborundum grains 1!' . 'er9 8.pplied to both surfeces at the l eading edgJ ov e r a surfac e l e ngtl:: of O.Ooc '11'3Bsured from the l eadi n g edg3 . 'This rou gtilless is d9fined tn reference 2 as the sta~ ldard rou l2;hr,e ss for a 2)+ - inch - ~hord medel.
The lift, dras , 8!1d -pitching !110lr.en t of the roodA l were measu red by the Fet~o~s dss c rioed in reference 2 .
The ailsron biLee - ·t;'1or~ent m08s'J.r~ments were :rr:a1e 'tiith electrical-resista!1ce strain gD.!d8 S r'ounted on the beams that sUD.1::)Orted the aileror; , 1'h1s method of mounting el iml n8 . ted the possibillty of fri ct ion due to the use of bearin gs a t the aileron hinge a~is. ~h8 pressure dif - ference ac ross th e a il eron seul was measured with surface static - prsssure orifices loc a t ed illside the gap above and belov! the flexible rubber seal.
Tests of the mode l 1'71th '3CJ.ch of th"3 thr ee ailerons we re made in the Lun81ey t1:,o - dirrensional 10w turbul en c"3 pressure tunnel at i~eynolds nurnbers of l x 10 and
9 x 10 a nd at ~ ,r. ach numbers of 0 . 07 and 0 . 17 , r espec -
ti vely . The t ests included TIl:=:asurerr,.ent s of lift , aileron hl~1ge mome nt , 8.1181" on balaYl~3 pressure J and airfoil pitching mOffi8nt for eQch aileron deflected in ~n cre - ments of 50 b e t·ween _ 20 <".nd 20 • Drag meaSi.l.!'ements were YY's.dro at both F'eyne>lo.s m.unbers throue;h th e complete range of aileron d=:flection for the rrodel ith the true - contour ai l e r on and , for the mo .e ls 1pli th th e strf:tlght - slded
and bev e led ai lerons , at a R'3~ ' nolds Dum er of 9 x 10
and 6 = 0 or ly. In addition , the moesl with each of
a th e thrse a11 '3 r01'18 "1-,8 tc S t 0d at a Reyno lcs ruy;]ber of ~ x lO~ with Rt8ndar~ roughn 0s s BDpli8d ~o t~e JGadi~B edge of the airfoil . rOr th3 airto~l wlth 13adlDs-edgs rou gh n 3ss , only lift , ailer::m hinge r!lom en t, ene ai.lf,ro n balance pressure "l'3!'C ·'n8t.'"sur'':ld through the r8.nf"! ~ e of aileron dbf l ections .
J'l1e followin£ , fector2 w?r::; aODli-sc to ' ~o;Tect the tunn e l data to fr8s - &i.r condltions; r7
o 9 r;·c I
cL'- • (: L
Cd = O.99 Lc4 I
o ' c. () CO:~r ' ID3;l \IT-;- AL
NACA ACR No . L5F27
= , nOoLq !
q a .J.. ' ~' ,~ whsra the pr>j,Irled quanti tJ es repres en t the vah:.e s measiJ.red 1n the; t1..mnel. (referen!'e 2).
PF~SEr~AT~or OF DATA For use in ajleron design , basic section data are presented for a ranie of aileron deflection in figures 3
to 9 for the true - contour tleron , in figures 10 to 15
for the straight - s~ded ailercn , and in figu~es 16 to 21
for tho beve l ed aileron . These fig1..Tes include data for the airfoi l i th aerod7r:&n:ically smooth surfaces and with standard r ou[hr:ess applleci to the leading edse .
flwse basic section data ~aJ be used to predict the section hinge - mo ' neI1 t ~hc , racted.st~ cs of il'3rons of simila r contour and cl:ord vii th D.ny a::10u..'11"; of s ' 3aled tnternsl ba~ance by the fol lo N~nt e~uations: ( l) ( ;) \ \ --- I aileron 'v'Thera incre~ent tn ai16~cn section hi~ge - ~J~ c nt ~oef ficient -· roduced b . y 8n ir.ternaJ.. - balBl".C8 arraIlg8 ' ~ert chord of ov ~ rt,an~ f:c-o'Y! etl '3 rQn hir .;e a y is to m:Lddle o£" scaled gap 0a ~~ord of aileron b e h~n~ ~in c e axis t twice nose r a dius of Dle1n aileron
8 CO rF'I :JE YT I AL
N~C A AGR No . L5?27 ~qustion ( 1), in which ths over~1an~' is assu:'1ed to eytend o the middle of t_be 6sP , can be used .i-or rie terminirlg Jhe overha:1g n~o:nents of E'ealed internally baJanced aile ro ns of no r m~l con:igur~tion, that Is , a~ l erons f or l.'.'hich the overhang e:xtends stra16ht fOT"':ard into the balance c~1a~.lber smd t ~1e se 3.1ed. gap vIi d th is 8:1"a l1.
The dgce. obtained at 8. F,eYl1:Jlds nurrber of 1 x 10 arc not so a:cu r ?te as lhose obt~l~ed at B ~eynolds nUl i_ ber of 9 x lO b h6C8.USe of th-8 s'Y1Jall clyns""'.ic pressuro , The results fo r t he lo wer :-\8~ 7-n ol.js number , hOY'8v'3r , are believ e d to be useful for in~icat~ng qualitati v e effects nf Reyno J os ml'ybel' 0;.1 the a:Lleron characterj stics in the rangp of Peyno16s nt'..,.b3r 1'1'0-:11 1 x 10 to <? x 10 .
Th8 effects of aileron cont:'lur on section ch ar - acteristi c s are co~~ared by rwans of section para~cters .
'Tari ations of these ,?arsr-et3rs 2lJd c08f'ficients wi th other i~dep enden t vari9.bles a~G ~re EP~ted in ~ra~n~ca l and t abl:.. 1 a.r for-n o Th2. fol::'owin~ disc.uSS- _,H 6re~er3 to h'3 C!.et3. obt8ine d.
at a R9"Jno l ds L-un'o e r 0~ ': x 10 w~ th tile & trfoil slU'faces aeroriynurri cally 5 '11 00 tn nl~le s S 0 t21'?rV'Ti s e ~ t a ted .
JISC 'J 3S::':Or~ A11er0n Effecti Ten8S S T!Je effect s 0 :':.' 81 1 ::;ron cor-to"i.· ' are s1-.lown in tq ~.) 16 II for the ai l sr cm section effecti ven es s pararr.etor a6 and fo:::, c1 and in fic3ure 22 in ~Iirich a i s -J lotted aga':'ns t o
0a at a consJ"bn t c1 ' 'Ibic~~8r-in6 or 1)'-:l1'f;JLl'_ t:1e ~Jrc..J ling
edGe of the ai l e relD r-esul ted 1n a decrease in oo t h 0'0 and. c1- ' The -& 1 '..18 of the cfiect1.Vel·388 p r·r.""6ter a , ,)
of each)of t-:-t3 t~1r 3c; ai l ::;rons tested vas sli.;~tly GTeate r
than the v8 11lv ( - 0.LS2) obtai'1E:C :-01' E. O. 2Cc. p l &in ai l ero i.1 of true airfoll c:)ntour nn &11 FL':,A 0009 [32rfo1. 1 section
(r eference 3) . Th« r'erCJr: t los~ in a.s ·~}ue to tra:L ll ng -
edge l~·.od::'fications to tbe trJ.8 C::'':1tc-ur ai l eron is ':lV-3 n in the follow~pg t ab le: ------_.
NACA ACP No . L5F27 CONFIDEl~TIAL Airfo il Ai l e r on
~ooth-
Rough True - contour 0
4·7
I
straight - sided I 1.5
4·7
Beveled 12 . 1 2 · 5
J
a / 6.
o \ The value of the effectlv9n~ss pararreter ~
e.c )
o a 6_=±20 a when measured over a range of ail(-ron oef10ction of ±20 at a co~stant section lift co efficient of 0 . 20 was greater for the straight - sided ai ler on o~ the airfoil with a s~ooth surface or v:i th lee .ding - edze rou6}:o..n~ss than for the other tvi10 ailerons . The "81ue of this parar.eter for the beveled aileron WES also great.:;r than for the true-contour aileron wi th the airfoil smootl: but ':"'3.8 ~ov'er "vi t!1 st andar(~ leadin r:: -ed ge roughn5ss apiJ1:'e'5 t ') tre airfoil. .An increase in t~e section lift coefficient frore 0 . 20 to
O. SO caused the 3ffectiven8ss ;&rBITster (~~0)
°a 0a=±200 to decrease for the true - contour aileron and to incre:se
:;1' ( t~~c ) straight - S;::dt;:db::::::da::::::n:~ q:::t;:::e
~6 a oa =± 200 able becau~e ).f a ;l:J'. in the lift curve at 'JL = 0 . 80 and oa = 20 (fig . 16(b)) . T~e ai l e ron effectiveness decre ased sliglotly 1 :hjn the Re n~lds mJyber v'as 6,
increased fro~ 1 x 10 0 9 x 10 as shown ~n table II
and fi.3ure 22 .
Section chara~ter18tics .- The effect of 811eron contour on v8r·5 ClUS ai lc:rOL S·3C, tion 1':1 r'6e-!rornent parair:eters
is u~e3ented in table II. C~~~:9S l~ t~e aileron contour
from the tru'3 [.ir:'o:i. l r:: 'LtO:~LL' ;:.~ s1-ralJ~t sides or to a inc r eased the V'::1.1U88 of c, beveled trailing ad6e -1a It is eviden t from fi~ure 17(b) and - I e) I~ASA ACR No . L5F2.7
that .tt e ej~act valu8 of c at a = 0 for tbe
h l) G , beveled at~er~n is considGrably les3 than 0 . 0069 as
gi ven in table :::::I but;, bec8use of t 11e sharp ci.l'mges in
the variaticn of ch with a near a section angle of o
attack of 0° , an aV3rE~ze :c-lciJ8 1;,£8 used for ch
. a between vaJ.1.:.3s of a of _2 Dnel 2°. An incresse in o
the geynol(s nl~ber from 1 x 10 to a x lOb provided a
positjve :.ncreo.se in C"'l for I:)J1 three ail"lrons and ' a for tho beveled a11ar.)n onl: (table II) . A in c1" --0 C01T.·:')al ison of the a:J.eron hi Dce7r:"0'1i('nt c"-1aracter'.st:1 cs
for - R Reynolds '!'lucrb:;;r of : x 10° if::",}'. iJ.., ll, ar:.c 17)
IT shows tha+; as tLe a:' :;'pro'1 ~"as i..;1~ic'~0red a~1.cl be s16d :rJ.ear t.J::.s trail::':rJ.g- seLzE', !";lb:::u,;,t C:~Hng, s in c' occur'rsd n in the low angle - of - attqc% ran2e.
1-_ co:r"'p8ris;J!'l of figures '7 Lnd. 20 S:1.0V:S that the
r abrupt changes ir:. 0 .., i')r th ;3 bEv'31 d aileron disappear ...
V'lhen rou::r,hness is a.)t~li'3d te' U"'e leac1':'ng edge of the airfoil. The h::'ngfS - !.'ow,:mt c~J8r·, ;:. ctt3::''''isti0s of a beveled aileron , therefore , ~8y b~ se~sitlve to wing - surface rcug~'me s s • [lata show:'ng t:le var~_6.tion of the increll'ents of with changes in tralling - e~ge angle of various a~d chB allerons on sO'r;',e NA.CA airfoil sect:i.ons are given in refer -
ence h. V~en b&sej on the change in tra!ling - edge angl~
from the true - ai rfo:1.1 contour , the lnc r e lne :rJ.ts of c,' and .l. ... c.
for the str .ight - s-tded flnd bevt:;led. ailerons with the C11
- [)
~ith standard roughn es s a:>plied airfoil ei ther sn:ooth or to the Ipading - ed[8 fall VIi th':..n th3 'S.Ypor:l.lY'entul SCB.tter of the dqt~ of referenJe b ..
The effects of .. eyn l~e nu~ber OL ~o/qo can be S8 3n in figure 22, 1-_r,('~ncl'e8.se i:n the Re:;nolds n'J' y,'Qe r
from 1 x 10 to 9 x 10° decreas8d tbe available pr088ure
differen e a~ross th~ alloron secl.
Jj8.Slf' for cc:,)..;:.:ri.'Jon . - ;-;-:,'" rat.e cd roll generate d by the 8.11eror h:J.s an. F port?nt e!,'i ec t 01'] t:'le hinge l'°')r~ic. n t because the r~t e of roll slt3r8 t~A n~an angle of attaok 6.t v.lh1ch the s.ileron is oner8.t:.n~· . 1''J1' co,tt;l8,rl.sC'n of' ailerons from sec ti on GE..TR; t!Jer:fo:..'s, hJ0 aiJ.-:.ron hirge - ~omen t chara teriST~cs are us~ally deterreined by use of
NAC A AGE No . L5F27
the cOl1etant -l ift concept , th~.t is, the assumption that l .
the aileron portlon of the ~in3 acts at constant lift during n steady roll . In reference 1, however , G2tes 8nd Irving iEoicated that the constant-lift concept o~erstrcssas the irrportenc9 of the hinge - wo~en t pnra~eter ch and gave the equ~1tion for' t'lG rate of c~·8n2:e of t.he a ~ - -
I
hjnge -- ··lo1rellt coefricient Wl th ailerc~1 defler;iion in s te !O~dy roll EtS -a cb ) - n-- c _
nO
r atter tr:'2.n (h) ·'VlJ.ich is the eqJe.~ion :'cr t~· cOl1st8!lt - l-:'it Gon~e-pt.
A:'_tl:ou_h equat ion (3) if:' ·::'1l'·\Ce=l1l3ie fo r co"""'puti g flnite - s an ctaracteristi c s ~ it is satisfactory for conp ar:LLg tllP t~ree ai Ie Y',:)::1S 0:' d=-fferent contour . 1:1 orcer to sirr.plify ibe o,p~ l ic~tttQn of e'-luEJ.tion (3) to nonli~elr curves , tte equation was converted to !J. C bv a r:'I J A t;~i0~1 va_ue f 1/5 is givGn for n in ref-re~ce 1.
-:;:':18 valuo c:)rres7Jo-r.r~s to e3v3ral .·:..rg - 9.:_lSron ~ol~"bjr_8t .. ons , one of \'·hi c ~"} is a v:jng ':·it~'} ~.n as)ect ;-·a:io of 0 Qr:d :-ith a 0 . 2Dc ~jleron ~~vinc -n eq~81 ~p - &nd - rlov·n deflactlo~ and extencJi.nc: :='ro'Tl~5 -)0::: C ' 3"1t ss .. lspan to tne v·L-:g ti,.
The value n = -=- "·3.8 nsei ij~ : e'.;.uatiJ.' (5) . '!.'~le , ~.
;18tr.OC] ot ant1.1:,s1.s l.'sed here'n is cor.sicered suit·3.ble faY' co ~pe.rin[; ih'J YlE:.lat~ . ve ~~ te ri ts of the; t}}ree ailsl"'ons .
'IDC anCllj1sis is £)r3sent3d in the rom: 01' the (;.;.q-c:i. V8 - L F1t clyt.n['3 in sect._on uri:;,le 0:;· atta.ck I-Q requ:1.r'ec, to o ./
rtcA ACR Jo. L5F27
maintqin a ~0~st3nt section lift coefficient for various def'le'2.t-i,oDs of tile 8ilel'on fro''1', neutral. The :t~in6e-'D1' ·Y'.er,t 6." T- .--':"~:T _ narCl"eter , 'yh:'ch IS the ratio of the i:1CT'8lY18Dt a l1 /llB a o ~n hinge~i.o~snt coeffic~&nt in sterdy roll (oquat~on (5)) t') the G.:t l erc effecttver.ess, is :,lotted. aga':'nst tLe equiva1e~t ~h8ng9 1n a~~le of ettcc~. T~e ~etho~ of analysis ta:~es int') a::;'cl'1.lrlt ':;[-.e a':"ler '-1 eff0ctiv·:mesS , t L0 hinGe "no::-~,er.t, end tl}e 0',)39io1,':o: ,. er:l18.rlir:al. ed.r8n·t'16 i3 'jetvI8.3Il l1.e cor:.t:r'ols 2"::'Q thr; Ll.l':I·OrlS. '::'.'(3 epan of thf) aileru'ls and poss:'b~e .. ~t'fe~t8 of tL:!."'e.3 - d:2.F::nsional flo':!
are no~ consi(er9d exce~t a3 ~~d~c~~8d in eluation (5) .
The s nJ.ller tt.e 'J811.:.p 0: +-l J ; _ ~ :c;C) - r o·'I"."nt p':',n:~etjr foj',' a C"'VO'1 '-~l'i.le of 'a J'\.. '6 'Y1o~'- a'~·'T ... ' .. ~-a""eou'" t"ne cC-Ib41~r> - ,., .... ~l ,,~. " u 0' ,.1. 'J, • to: '.'. <-c __ v CAe ;:, u ., ~ ,,-,. - tion shouLi be f''):.'" 't-r·ov1c:;'ir:.:- c:~ 10'1'(;r control f'or~e fo r a
gl-.ren hf,lix ang le of th e i.n'ill;S tl,J ~
2V Plain aileron. - In or~er to corrpare th3 D lain ai l erons of cifferent contour, V~J.Ue-:; of t'.O h~n£e-mor,le;::t ~arameter 6. C T..- ""T o re plotte d B~~inBt to.. in f'l[Ure 23 .
~i2'ur'3 23
o icld.icate8 that t'1.l.CkO·::.:i.::1f: and cev'-'ljng -ebe tr'D.ilinc' edee of th'3 8.:1. 1 ei 'o n would l ,'1,::>ro v3 tree cor,trol-force charL.e t8r - is~ics of a 8eeled - [8.9 O.20~ rlsin ai l e rop. r;:-he 9.j:plica - r ti on of standard :::"oughnec s to t hG [' i 1'foi 1 C8',lSeS the 'cl.n .:8 - n."):'.If':.1t )t:.rar:1J+-r;.r ::'0 ce,::,-r('8S') .. n !lqt.r1 t.udt:) fl ....... ~ E~a11. v:3..1I.lI~S Q of 6. ao and to in~re aD~ for ler~e values of 6 ' o p~l'l"'ce,'l n " l """nn - ]:'o~ c,,"""C1l"o"n"l of' l-:J. ..... t'·'l'r.,,,, .::;:,.Q...,40.v .. :t c::.l. J-'-_ • • i ~""""':::.-""" ~! ...... __ ..L v_ ...... · _ ,-.c ailer:ms of :iiff'3:i.~~r! t cnr;tour 1,':i th 88(' .. 1 0d :'nternal ba Lmce , th e ef":'ec ts of s ',n:-11l cnc.r... [·33 i rt t::e pro S S'L..:!."'e cti ff 0 !' c.nC3 aGrcss l.he Jj. ler)l1 seal 8 1' : '3 chrng-"s in 'ririb rou "mp88 e're
c
i '·!~orta~lt . Par a. cor.ser"cti V'3 de::;' hD, tr.e ::"n:er~1.n.:2..ly ba 1 D.l1ceri. t::'i18}:'on "1~lOuld bE! 10 pro). rti'):'.Cc! 3.3 to s.vnld l over·baL_~nc.e .,./re.l'l the v:': C ra,3 t:Ca IOl.<!l1Cst s'u·[':-.c·, ~tt:t w:'L':'~cl 'be CY'J8 ted ~L Ser"iC3 . roy' r~le G.1.:c'foil 1,,1·.th st ardard lesd·ng - e1~e rcu~tn8s , ~~c c~ord 0: oV8~h~n;
cb ne~8D2ary to balar.cc each ~Ll~rcn to ch_ = - 0 .001
arT' W3.S cc '·,''')ut.:;:d u'~ :" ~ "l'S ').:' the fcllovl··~n..; eq:,J,8.ttons :
Po lie;) \2
( 6 )
- c1l '.,' _. , A + '2 -1 I, c~ ;'
no •. ,,_aLc,.... _\ CJ.i.~r'I D3.: r:;:':U.L
N ACA ACR N o . L5F27 CONF I IJEN r=A L 13
( 3) The corr.::nlted overhange cb/c9. rera 0 . 53 6 , 0 . 531 , and 0 . 396 , r"lspecti,\Te 17 , for the tY'ue~co"i:;tour , stra:. .g h t- sidad , an d be ve2.ed a ~ le r ons. T~18 hln~e - roo 'EL t c oefr.:.. cientfl for t he an is Ie; - of - 3. t ta~~ &l'1d ai l e r ')l1- de::l '''C ti on r ane;e. S W"lre th~n calc'latd~ froM the 6~ta O~ the hL~gc - rr)~cnt and se~1 - Dr 3AEu r J - ~if~er6~ce coef~ L clents for ha olain ailAr~n b;; use of 9-11)8 tions (1) and (2 ) . ':rhe ~ppr')xlma te li r~ting def l ~ctions of t~e t hree s'e13d irte~nL l ly balc.:n c eC1 ai l eror.s ' f tr".l "3 ir' .'c,j l conto'lr, str~iglJ.i:; sirles , and 8 'oAvolt:>d tr·R; ' ;r1CT (' n' ~ -e \/ " -"'.r: +lC ,O +.1,,-0 :~ i 1Q - ± JOo • ' 'J \. v - ~ . ..1.. - " c. '" ·c, " ... \- _ _. .J , _ ./ , ...... - c:.. , respect::vely . 'Th3 ::-::axi·,·.;'Lr! .ie1'lect::'ors.vere l-tl.:i t 3d by the len b ths of the sealec. int e rEal balauJes .
F')r comDari SO:l of three s ca 13d internally calanced ailerO~lS , val"L..es of th8 rin;?-.e - - :o'''en t 'Ja "Y> a'1'l':!ter 6c,· ~ ) -' 7I. ~ ~ are o18ttec, a.;ainst t.a'") :in figure 2Lj, .
11 a of /~ 0 e.
C F':l[ ... ure 2).' .s"lJ.ows tbct t'1 ' C! Jr'l:?b t - 8:ideri .il3ron Y 8''lc l,ld ',):rov:1 de t''18 ~1'i::3.1~,est ccp.trr:l fo., Cf: of t hp. three sa8.::'ed 7.::",tE.r'r'}.:..Jly b2::'311Cec' all-rons . 1'1-).e order of meri + . of t,[Le three a-;, ler0ns C!lar:e-pd T01hen the internal balan c e wss ~d~ed because of . ~~e effects of 3ileron con -
. 1 . .., f - I -. #""i f r' .,,, t
t th ou r o n '_ e ~iva1 .=t'LG ,33&1 - ;JresG.lre - ul ~i e r'e"lC8 c.,), , 3, 11C18n
at the 115 gh-:or b.i13:!"0l': u"flectJ,CD3. Fo::' n V'.inC v:i th 8 s :nooth8r sl]rf~ co ,: _ aD t::at for '!Tl~cl: the cODso r vat::. ve ai"101:.nt of s(:;l'!led t!i+er::u.l ba:i.8LC" ~·:as .:1pter.'1~ ed , th9 control rJrce irl t ho Etr1.~~t - J·ded riler'D v101( c':lar.~,e t~'.e le::u :lt of the L. rS] :,ilerr)ns, 'Iris small ~:-::::cfE:, in t:t e ccr.trn'l fo)'"'e;e f(n th"l straicht - of
sided aile r on can ~e seen in figure 24 by a cow~arison
cprr.
~
tor tlre smootn airfoil wi th those t~e values of'
a 6 . /!:. 6 a I'fJughn8::iS.
for t"lJ.e Jir f' n il wi t tl sL":,,dE'r.:.. l:';'3dlEg - er'l.z;e CCNFI T)E£ ' TIAL
j
N ACA AC R 10 . L 5F 2 7 ':I'Le effelJ ts of at le rem contour , Reynolds n'.L. .l ber, and standard airfoi l leading - edse rOl."lghness on the li ft - curve slope C 1 for tl-:e "'SACA 651 - 2 10 airfoil s (3 ctiol1 vdt~l the . Va a1 113 ron mm tral are show11 ir.. t Slb2.e II. A s tud'Y of table II shows that c l is ~hang2d by eittsr roughness or a ""~e Y110 1 ds Tll,l'('CS:c' by l es s t':1on 2 :JeI'c·snt reg3.rcless of the nllaron contour . A rec;,v c tt on . ~n 1:] . ft-curv~; e 10I)e , howeve r , of 8."9prOX 1 Taete1J 2 and 7 j)e:r:IjE':-:i". , r~3"}1:;ctiv8ly , resulted.
wl'.en the f.uJ.eron W6S c':-~er:~~G i'r,)lrl the true p.irfoil contou r to s trlJ.ight sid'3J 0:" -::'0 a be\e18d trai . 1in(; 6Clge .
A ' 0 ' -".,..,~ s n 0.P {'{ (~"'"Y''''''' 3 Ie. and l ~ "'ho ,n +-hat f'
l-l. C mI-, 8 ~.L 0 i ". ~ _. c ,,~ ~ ..:: , _ v , • 0.:> , ....,.: '" " .. !' u _ 0 I" the airfoil vei t h stl1ootl~. s·u.rf9.ces tt~e maxirr.UfIJ sec-cion lif t coeffic i en t of' the l\'!",c,;. 6:;,, - 210 ciirfoil se~tion ~.'i t h the a1 1 e r l) 11 n eut r a l Vias 9.,;'prox!mc.tely 5 percent less for the :!11 . ode l vl:l t h t h e 8trG.lg~lt - si..ded or Leveled ai 1 e r o!13 ths.:n \'.Ii t h the tr ue - c::mtou:::: ~=::'L l sron . 1"h13 108s in maximurr: se c - tion lif t. coefficient 1 3 B.lJtrib1.lted t.o the c hanc;e i n
c pmbep o v er the r oa r ") ar t or thf) ai rfoi. l sec ti on c aused
by the ai l oro n- con tour rr.odli'J c 9.t.i on . 11 compari son of i:! g - ' 9 ) t ), t- ,' . t1 ~ f . ~ . tl,.
d ures . , . J Hn' ..L snows .. 0. v 1 lor ne B.J.r Ol l. W]. LL 7 13 st8ndal 'd l eaoin::; - pdge rou'0:hn~sa , t~e :rnaxirrU1:1 s'::)ctlon lif t c oe f fi ci en t was tr_8 sa:r'l .' 6 for t:J.e true - ceutoll.r a!1Q straight - sided ai l eror .. s but t hl3.t the max:1.Y,ll.)Ii1 sectio_1 l ift coefi'i - cien t fo r the beve led G. ';' le-ron was les s tha:1 the. t for tl'F' tr u e - con t our ai l eron .
Pi tching N.,)Yc'Cll t The eff'S ct of aile r o.r1 .:-;ontour on the airf.:::ll section pi t ching mOlc6n t ~3 shovvY', i~1 table II L.nd fiGure 22 . The rate of c hange of c l1" c/L~ with c be,oe .3 s l ess n eg at.1\-e , L which (~(lrres:roL 18 to a for" ; ~l.I'd. 21--Lft i.n t~Je ae:::'o(l'jl-:ai"'1ic a en t er , as the a!leron centour 1s c~~nged fro~ the true airf o i l contou r to straight sldss ~r t.o a beve l ed trailing edbe . 'Ihis c:b.&ng'J in aer:)cl~~n8J:)1i,') cen:: e r 8.i;:I'89S wit.h the results of re:f'cr·:;r;ccs ') o.nd 6 . F.l1 i:"lCreaS3 in the :1 0'mo l ds numbG r frorr 1 x 1·:)0 to '1 x 10 h3.d no ap : )Y>ec i nble . ~
effec t on the varia t-i .. 0:1 of c ) v;i t h 69, et a Gons tan t
rr
'c/ L
sect1:)n 1 1ft coefficient 0 f 0 . 20' (fi Z . 22) .
corIlj)SFTIAL NACA ACR Po . L5F 27 CO~JF'IDE.YrI AL Because the chaf'ges in section pi tch.!'Lng rnoment of an alrfo il inc..uced by a il eron d'3fle c tion are of primary i '~po r t anee in deterrl1ininc; the lateral - control reversE,l speed , the v'3.riation of the increrr.ent in section pi t.cllinC -
moment coeff i cien t 6c 14 w:L th the equi va l ant change in
m c t section angle of atta c k required to ffiaintain a constant section lif t coeffic i ent Jas plotted for the t~rea aile r ons (fig. 25) . Th:; variation of DC~ , wi eh nao "'e/4 was approximate l y the same for t he three ai l erons tested ( flg . 25) . The rate of Ch8:c:g8 of 6c'11c/~ . wi th 6a o i3 0 . 0205, 1Jt'~~ch agrees lnTith the theoretica l enG. experi - mental values giv~' in reiere~ce 7.
Drag T.:.1e effe~t of 2.ile::--on Jont:Jl ~::-- on the airfoil section profjle - drag coeffJcient is presented in figure 26 .
V,i th th e ail:3ron n su trsl , changes in the 2.ileron contour within the range lnvestigated show no sigriifics.n t effect on the airfoi l sectlon ~r file - drag characteristics .
Tne variation ')f airfoil section profile - drag coef - ficien t Cd \"i th f:lect':"on an21e of attacl.:: an for '0 .
various aileron deflections j.B presented in fi.gure 6 for
the true-contour a:!.leron at Reynold::: n1J.m~ers 'J i' 1 x 10
and 9 x 10 . At a P.9ynolds mlInber of 9 x 10 , a low -
drag II bucke t " ",'as re f;.li zed 'Ott all A.i leron detle c ti ons ( fiC; . 6). Because t.he ~hange in cel v'~th a5.1eron con - o tour was 8~all ~ith the &ilaron neutral , the section profi l e - dr~g ~haracteri~t5cs of the airfoil ~ith either the stra~ght - sided or beveled ~i19rcn deflect3d would probably be t:-1e 89 .'1'e as for the air!'oil ''11 th the true - contour al leror: .
80NC :!:"U';I OrTS A two - dimensional ¥1ind - tnnnel investigatloTl WaR )""'3..:1; 'Jf an I~A(;A 651--210 :;:.} rf oi 1 equipped ,.'1. th three inter - changeable sealed - 6ap O . 20 - air~oil - ~hord plain ail'3rcns of diffel'en t coritou r. The irfoi l lNBS tested wi t h srlooth surfaces and wi tr.. s-l:ar..dard l eading - edrJe roughner:.s . fJ.'he data obtained indicated the followinG conclusions: 1 . Changing the al 1 eron contour by thickening or beveling the trai l ing ed;e would cause
NACA ACR No . L5F27
(q) Tha ai l eron section effectiveness pararr~t8r Q5 to c:ecr<;)::ise (b) The rate of c~ange of ailer~n section h~ llfe - 'TIOl""snt coef1'::! cient c }) 1I"i th both sect::'on an c;le o~ rttack Q and ~ile~on ~efle~tion 6 to a innresse pos1tjvel~ (8) ':.'11.<3 rcd.0 of cl"H'l.i- ... ge Jf s9 ... tion lift co(ffi -
ciant Cz ~lth se~tio~ ~~sle of atta~k a to
o decrease (d) The mp~i~u~ s9cticn ~ift coeff~cie0t to decrease (8) '].h3 f:erJd:.nemi.c csnter to ~hlft forwa.rd (f) ThIS inc::,elr.pr~t of 2'3ction -ni tch:.ug - ;non,ent coeffic!eLt in~uc9d by a1l6ro~ deflection at con - sta.nt l:":ft to yerra.'irl the same
(g) 1h3 s8ction )rofjle- 6rag coeffici5~t wit~
the r: i 181'on nen tr9.1 t:; l.'en _8:~:1 ~ uba -t~. ntl ally uLaffec ted thronghou the 8e·~t:ton )U'[,:,J.9 -oi - qtta ck ]"",pge 2 . ']lhe arplicc,U 0~1 uf r;w_"'rr~"l3G:::J tlJ tr ... e leading edge of the air-fall woulo. g.co Gr. tu':.1. te the balcnl.ci n6 ~c t ion 01 th8 aj ley-on .ncl the; 103 s in nileron ef::'ecti veneS3 caused by beve ~iDg tIl e a:t 1 e Y ' on tr -81. U rl'::: W<iSe .
3 . 'Ite :::ffect of s.ilol'::m contour O~1 the hinge l" 0lT.8nts
of sealed i~tc ~l 'nallJ balcrc3r1 [<i ler r.s, 3.3 COT"': putsd from ds.tr1. 0~1 the h::'nge - r::.olYent end seal - oressure - dlffer'enc.;e coef - ficients of nlaln njleron"' , sh.owed cn aPDreciable ~:3:rfe ct o{ cilerop C0utour on th8 hiu 36 xo~ents at l .rcs a!lGron def'l c ctj.oLs even thOl.:.g!l ~~ ll t:lY'ee ?i l eroils W'3re CrlllJ)U.toil to hClve tl ~.e sa"'1e hiq:::e: - ;Cl?:1Srlt ~2.0?~ I- t '3'''':'11 deflActions,
Lanbley i:f''''::ni al A 3rcnau t::. cal :,[ t·:) r torr
Netionel ~dvisory CCl ~~i tt ee for Aera]~utics
L2i1€ley T':'.eld, ,T 8 •
conFIDENTIAL NACA ACR Nc . L5F2 7 1 7 REFERENCES 1. Gates , S . B ., and Irvi n g , H. B .: An Analysis of hileron Performance . 465~ , S . & c . 1 154 , Rep .
No . B.A . 162L~ , Bri t ish R. A. E ., July 1 940 .
2 . Abbott , Ir& H ., von Doenhoff , Albert E. , and. Stivers , Loui s S ., Jr .: Sun'mary of Airfoi 1 Data . NACA ACR No . 15C05 , 1945.
3 . .Anea , ~[ilton B ., Jr ., and Sears , Richa!"'d I .: Deter- wination of Control - Surface Characteristics from : ' ~ACA Plain - Flap 8.nd Tab Dat& . RA.CA Rep . No. 721, 1941.
4. Purser , Paul ~ ., and Gillis , Clarence L .: PreliMinary
Correlation of the ~ffects of D3veled Trailing Edges on the Hinge - ~:omen t Charac teri Stl.CS of Con - trol Surfaces . NACA CB No . 3E14 , 1943 .
5. Cr·ane , Rober t v' ., and Holtzc l aw , Ralph 1{ti . : Wind -
Tunnel Investigation of Ailerons on a Low - Drag Airfoil. I - The Effect of .Aileron Profile.
rACA ACR No . 4Al~ , 19)~ ..
6 . Purser , Paul E ., and Johnson , Harold S .: Effects of
Trai l ing - Edge I i' iodifications on Pi tchlng - '- oment Characteristics of Airfoils . NACA. CB No . ti~I30, 1944 · 7. Purser , Paul E ., and ~cKimley , Elizabeth G .: Com -
D3rison of Pitching M o ~ ents Produced by Plain Flaps
and by Spoilers and Some Aerodynar.ic Characteristics of an NACA 23012 Airfoil wi th Verious 'Types of Aileron. l '! _·;.'JA ACR rIo . L5C2L~a, 1945 .
CONFIDE NT IAL NACA ACR No. L5F27
TABLE I
ORDINATES FOR NACA 651-210 AIRFOIL SECTIOH
~tations and ordinates given in
CONFIDENTIAL
percent of airfoil chord]
Upper surface Lower surface
-.
Station Ordinate sta tl on Ordinate
r
0 0 0 0
.819
-.~19
.~3c) .~65
'B
. 22 -. 59
.999
1:ll9
1.273 1·331
-1.0~9
1. 757 2·592
'\ 2 .~oB
-1.~ 5
4. 98 2.1+91 5·102 -1. 59
-2.221
3.069 7·606
7.~94
10.106
-2·521
G' 94
G' 55~
1 .. 899 15. -2. 2
·33 9
20.091 -3.3 .6
1+·938
1~.909
2 .921
5·397 5 -3.60~
2 'OlR
6 30.0
2 .93
5·732 -3.~8
049 -3· 94
4 5
3 .9~1
a .
~:6~4
0.032
-3.92~
~.9 8
'.• 984 6.05~ 45. -3· 86
50. 000 50.000
-3·709 -
5·915
5. 54·986
~5.014 -3· w· 35
217 - 3 ·075
0.02l
G·
~ c. : § lt . 712
-2.6~2
65 " Ol
-2.1 4
70.0 3 4·128
6R· 9 57
-1. 689
3.4~9 7 .95~
l5.0~
-1.1 91
0.0 ~
2·7 3
~~. 9 5.
8 5. 3u 1. 9 62 -·711
2.057
gO.028
1.327 2 -.2 93
8 t· l
.622 . 010
95. 01L ~ 9 .9 6
100. 000 0 100 . 000 0
L.E. radi u s: 0 . 687
radius t hr ough L. E. :
2·1ope of 0 . 08425
~ - NATIONAL ADVISORY
CONFIDE N TIAL
8mfM I 'I 'T EE F OR AER Ot ;AUTICS o r-' (]I 'Xl (\) ...:J z :x:- C) :x:- :x:- C) :::0 z <.0 I--' I ---- 0 .
m -.0100 - . 0104 -.0098 c -0.0100 -0.0094 ------- -0.0086 --- UTICS ma -.0008 -.0002 0.0010 ------ -.0001 c
-0.0007 ------- standard
-0.0017 ------- ------- AERONA ADVISORY FOR .074 .077 with 0 .075 Po ----- ----- 0.079 ----.
0 0.075 0.074-
= 0.80
and NATIONAL n = .024 .024 .025 0a P
----- ----- -----
0.025 0.029 0.026 cL COMMITTEE AND hO surfaces AND c -.0059 -.0122 -.0l~4 -.0110 -.0113 -.0100 -0.0112 -0.0070 -0.0136
=
O 0.20 n smooth
Cl
.0019 = ch -.0062 -.0092 -.0040 -.0071 0.0069 -.0°27 -0.0066 -0.0050 AT AT aileron aileron =t20
•
(~) aileron ) -0.470 DENTIAL o -0.449 -0.480 MEASURED a FI
---------- ---------- ---------- ----------
Ma ---------- ----------
aerodynamically
(6
MEASURED CON Beveled CONFIDENTIAL • with ) True-contour 5 straight-sided 6 (2 PARAMETERS =t20 --
• )
-.435 -.480 -.400 -.454
O -.428 -.480
-0.459 -0.455 -0.4 -
~)o dO. O.=±20
- airtoil
CCl
(::0\ ~
SECTION the nO -.450 -.450 -.485 -.415 -.475 -.49 -0.460 to FOR -0·472 -0.465 11.- L .042 .047 .049 .053 .047 .051 c 0.046 refer ness.
TABLE EXCEPT gh .107 .106 .105 .105 .100 .099 cLn rou 0.106 0.050 0.100 0.108 0.052 6 6 " Rough" 6 6 6 6 6 6 ~-~ 10 10 10 R 10 10 10 lOb 10 and )( )( )( )( )( x x 10 ~ - 1 x 9 9 1 x 9 9 1 9 9 ~ 0.80.
0.20.
leading-edge = = (1) cL cL Smooth Rough l"Smooth" 3 ~ough Smooth Smooth Rough Srr.ooth Smooth 2 Surface Smooth -
_
- z » (") » » (") ::0 z o r (J1 'XJ C\) -..J 'XJ ..... I-' CJQ ..
the in tested tunnel.
as pressure aileron, with section low-turbulence CONFIDENTIAL airfoil -210 two-dimensional y NACA le g 1.- Lan CONFIDENTIAL ure g Fi Fig. 2 N ACA ACR No . L5F2 7 CONFIDENTIAL se al.
(a) True-contour a1leron.
t- ------- .200c .003c seal (b) Stra1ght-s1ded a1leron.
Radius = .100c Hinge axis (c) Beveled a1leron.
NA TIONAL AD VISORY COM I4 ITIEE FOIl AE RONAUTICS CONFIDENTIAL Fi gur e 2._ Sk e t ch of the three s e al e d- gap plain ailerons an the NACA 65 1- 21 0 airf oi l se ct i nn .
NACA ACR No. L5F27 Fig. 3a [ CONFIDENTIAL. ' :Ii , I _.
- F ' .
R'
~
.
True contour f .~ -- • Q , ~ = • , t, ) i tV-, I ,"y t v' lli ..
,; 4, ;i 'i. 3; [ :li- • : !?'~ ['t' !'
... e' .
- p-;, ., , ~ :J!
1, I h' IJ
, - J
",il i i'1" 1 !r , 'A "b. H .
- ;u f ,I 1) h o ' iI --' ' 1 V !>< ~ 3
"
r~ ~ r.; '~ / :p I· '\, ' (de:) I i d l. A l .. .,..
-.-'- +- • '- ;.~ <:r' a..:.. ' " 0+ I f / 5 -'- ' r '/-. j " . 4-
, .. " ~ ...r<
...J... I I 10 ..[
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, . -:.+ "",-, ~ , NATIONAL ADVISORY ;. ' : - - COMMITTEE Fot AERONaUTICS - 'T"
+
CONFIDENTIAL ~
ilfl ~ -<- " ;N
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J - --oc-
, Section angle of attaok.
I a o • deg Jrf- T '--_ --L--+-: I I, 1,' _ r-r":T:I r-r: T T rTTT J.~ L I I -~ (a) R = 1 x 10 , Figure 3._ Lift and pitching-moment characteristics of an NACA 651-210 airfoil section equipped with a sealed-gap 0.20e plain aileron of true airfoil contoQr. Tests, 'lDT 847. 849. and 850.
NACA ACR No.
L5F27 Fig.
3b t--r-' -1- 1--1- iV t-- t-- - t-- -- -I- _0 .
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NACA ACR No. L5F27 Fig. 4a , liP iii P iiiP!i I'i!'
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i6 2 , -B L I I i ll i !1-1~ .. ..l 9 :0 .1.1 H--t-t-t-t--H-+-.-H--t-+-H: Section angle of attack, Cl ' deg c.~ NATIONAL ADVISORY -r- O LI---_ 1 _.1-_ f U. L.._ L' L L..:.L_l-L.J J,!...;' I -...l..!.-L L •.. L.......l ...J .L 1 .L.._ I L.. I _. COMMITTEE fOR: A£RONAUTICS !
(a) R = I x 10 •
Figure 4.- Hinge-moment characteristics of a sealed - gap 0.20c plain aileron of true airfoil contour on an NACA 651 - 210 airfoil section. Tests, 'JDT 847, 85~.
- - ~ ---- .-~ . ~ ---- ----~-- -- --- Fig. 4b L5F27 NACA ACR No.
.: ..... II .l ... Hih..J l I TIT J:J I J I 'I i H+H++'-Hb+H++.d. CONfiDENTIAL +: '$H4-H48=P+$H4+d ",,"H++d448edFI I-r-: ,. -. '.. r- . ,J: True eon tour I :",r-'~ .1 .J .-t- I-+- ~ .
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-
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Section angle of attack, eo' deg I ,.
+-.- I-+- -'-- I I' I I i I Til I-r:=-I~·I",J.''-+--'-+-f-f-Hi-ll- I I NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS (b) R = 9 x 10 .
Figure 4. - Concluded.
"III Fig. 5a NACA ACR No. L5F27 I tiitltl1 fn til ~ ~ tf ·.~ L = I ""=1llI f!:l:i~1:io ~1.\:!
1>l ··~-fij.~l I:I:tj 1 '1: ~ co nt o ur It ~NTIAL Ii :1'1 :lJ: .- 1 ,'ilO ft· i'ti ~ ) 'E~tt!h ' ... 1J: ' . I.t ftc ;:<., bJ... o tt . l iP.
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. A'l :l r "' · 'tl I..;;i IY 11
6: Il:t.., r.";: \'- 1W'tf; ./ I ~ I ~ 1 J±tl r H-+-+--I-+-l- "' -I- " +-H-l--l-+-.J-H-l--l-+-+--1I-+-+-+--I-f--j,...,q. F'l -+--+---=.J ' NATIONAL i-'-- V COMMITIU FOIl AERONAUTICS , I CGllt DEN U,L 2 I I': -1 ' 1 1 -11. 11 '"' t jctlon angle attack, a ' deg !:-+ I -l- -+- +-H-l--l-+.:!J o T-r r-l r"l T T I' 'T r r r 1 I· It I I I I I I I I 1 "} I I I I I I'-.--"---J.- I I -"--'---'-- .I.....-J.- ... '---'--'--" +,., l:...-J ! I (al R = 1 x 10 • Figure 5. - Pressure difference across the gap se al of a O.ZOc plain aileron of true airfoil contour on an NACA b5l- 2 lO airfoil sectlon .
Tests, TDT 847 and 848.
NACA ACR No. L5F27 Fig. 5b ~ . -4t >j Fe! '1 _"i '1: i t :ttcrw ,f!
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III 11 I V
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11111:lllf,l
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NACA ACR No. L5F27 Fig. 7 True contoUl' Standard L.E. roughness
i1 -~2;£;.1 "! i:l- >4 =tat P.-
_~ d[ D-i+l-+!=R-!-H+R4H~~~
r:t+t ~. t~ h f:l: ~ ,t r' .,..... ""Tt ll I -H+ .-' T ... ,~ :]:it- j: $:r~ ~~ /+ jJt 1. t:r: -'1 R- -!i: ~I:t -;:f: ±: ~~l ~ ~:t':::i'+:- iii.: 1 M- .
:E :r l-,:;c fU Figure 7.- Lift characteristics of an NACA 651-210 airfoil section equipped with a sealed-gap 0.20c plain aileron or true airfoil contour. Standard leading-edge roughness; R = 9 x 10 ; test, "lDT 869.
NACA ACR No. L5F 27 Fig. 8 . , i,,,P,.I"l ·!;if· r'H!' . fJ': ..
. • :~t:d:; I'"' .... ,.1; Ie 'w
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: CO~ 'I DENTIAL •• . ,:~lf'; .' ,.:,.'Ii:'/W
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True contour ,;.' .
Standard LoB. r oughn ess 1"0" ",I:"!::,
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T N .i.
1-++-t-I--+.-.cI-+-+4-+-+-+-+.H-+-1-:+-l-H--H'-I-+-t I'--,;,. ->I""'· 'I'--v-¥ y ¥'fH'- -~ ~ "- ~ ~~
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1 I I :> I-H- I I I I I-I-t- L.L.
Figure 8.- Hin@O-moment characteristics of a sealed-ga p 0. 20c plain aileron of true airfoil cont o ur on an NACA 651-210 airfoil section havin g stan d ard leading-edge roughness. R = 9 x 10 ; test, TDT 868.
NACA ACR No. L5F27 Fig . 9 I • " r tf l- I- t- I- [t ;t .... I ~ -
I-
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- "
l r'!.
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I-- I~ NATIONAL ADVISORY l--' h- l- I--- c- o COMMITTEE fOIl AfRONAUTICS ,1., -~- . g, -, . ~ . I-~ -1 ~- -
-
1- ftEt- '-
I Section angle of attack, <1 , deg . t
1 .1 " [.
1- f-
-1=
YI TfiIJ' t-I-~
CONFIDENTIAL ~ __ _
tLL-'-
Figure 9.- Pressure d1.ffereoce across the gap seal of a 0.20c plUn aileron of true airfoil contour on an NACA 651-210 airfoil section having standard leading-edge roughness. R = 9 x 10 ; test, TDT 869.
j
Fig. lOa NACA ACR No. L5F27 ~-+~-- -r- --r- r--
---~t-- -r- --r- r-
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I- - -- -f- r-r- -'r - r- -, h - :;: - -r-- COMMITTEE FOR AfADN rr AUTICS -j---
-;--r- --f,.."lI- ---I- -t- CONFIDENTIAL ill ---<-'----
r-1-+--I--+- I J. r - ~~-rl , ~ a 1 .. : - -1- ----
I- _++-+-_H - I--+-I~+ H-- --I-- Section angle of attack, <1 , deg + I I I I
(a) R = 1 x 10 .
,Fl~e 10. - Lift and pitching-m0l4ent characteristics of an NACA 651-210 airfoil section equipped with a sealed-gap 0.20c plain aileron with straight sides. Tests, toT 8)4, 861.
NACA ACR No. L5F27 Fig . lOb ....
. ~.
s:I ~ . , :f
J~
orl '" a j """r..- l e_ , t :1 " ~
(b) R = 9 x 10 •
F1gure 10.- Cono1uded.
-[ NACA ACR No. L5F27 Fi g. lla Figure 11.- Hinge-moment characteristice of a sealed-gap 0.20c plain aileron with straignt sides on an NACA 651-210 airfoil section. Tests, 1DT 852 and 860.
NACA ACR No~ L5F27 Fi g. llb Figure 11.- Concluded.
Fig. 12a NACA ACR No. L5F27 , - I- :- - - - ~~~~~-~~~~--~+-+-+-~~~-,--t-+-+-r~'~~+-+-+-r-~~-+-4- - ~-+-+-r-r~~-~+-+-+-~r-I:-~-+-+-+-+-r~~~-t-+-+-~~~+ '- - ,~ I-- o- c- - - i I--
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la) R = 1 x 10~
Figure 12.- Pressure dirference across the gap seal or a O. 20 c plain ailercn with straight sides on an NACA 651-210 airroil section. Test, TDT 854.
Fi g. 12b NACA ACR No. L5F27 ~ r t' I1J f1!! r ~['1 I 'f:~\ fl',, : '! f4j i;' ,' <:= n< mi l k :,:1 l tH riit:c , f\: 'It, , t-i i..r..
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, -- AOOIIAUT ,(;091"1 Itt 1 2b I - I -L. ·I I Section angle of attack, no' deg + ', -,. I I I I , ' =1" I ~r ' I , . , " r tl ~ • T T I I .1 1 I I, 1 1 1 1 I l ,i I (b) R = 9 x 10 • Figure 12.- Concl uded.
Fig. 13 NACA ACR No. L5F27 Straight sided
Standard L... roughness
CONfiDENTIAL ~, :!=i.'" 0-
°a
(deg) ..
I" 1 m
~ Q CI
-5
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-5
-10 -15 I=H:t -20 ::;: ;t: ~:t:' Figure 13.- L1~t characteristics o~ an NACA 651-210 air~o11 section equipped with a sealed-gap 0.200 plain aileron with straight sides.
6; 5h.ndard leading-edge roughness; R = 9 x 10 test, 'lDT 864.
L-_ ~ ______ _ __ ._- --
NACA ACR No. L5F27 14 Fig.
Figure 14.- H1nge~oment characteristics of a sealed-gap 0.20c plain a1leron with straignt .idea on an NACA 651-210 a1rf01l sect10n having standard leading-edge roughneas. R = 9 x 10 ; test, ~T 863.
Fig. 15 NACA ACR No. L5F27 CI "D ' ":1-, V " ~ ...
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Figure 15.- Pressure difference across the gap seal ot a 0.20c plain aileron wit h straight sides on an NACA 651-210 airtoil section having standard lea.c:ling-e~e roughness. R = 9 x 10 ; test, lDT 864.
NACA ACR No. L5F27 - Fig. 16a p ~ It f'+ EI ,
:~ , 't!4 ~# ' I ~J:l1il rm btl
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~; -, ;- ':i~ Ifu :mi t!:IJ I ~\ l fit II I '· tr' l ' f l:!-' , I tl~ l@ I ~ ~ ttt1 : i It ) ' I ! 2i !it Seot1on angle ot attaok, a ' deg I t 41 ; 1 k ' ,~ o L' .L<= ~ : , L ,~ •• _ ~ (al R = 1 x 10 • Figure 16. - L1!'t and pitohing-moment oharaoteristios ot an NACA 651-210 a1rtoil equipped with a sealed-gap 0.200 plaia aileron with beveled trailing edge. !8at., 1P~ 858. 859.
..
Fig. 16b NACA ACR No. L5F27 I "· j:!: 1* Illiild, , 'I' ' '1 ii ~ h [..
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• ""~ It If£l., k (b) R = 9 x 10 .
Figure 16,- Concluded, NACA ACR No. L5F27 Fig. 17a prj Lin:: I .
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Eli 1';" l,~V' ' , ." , -..- ' ." , ', , , '" Ii· ,"" " (a) R = 1 x 10 , Figura 17.- Hinge-moment characteristics of a sealed-gap O.20c plain ailerCll with beveled tra111ng edge on an NACA 651-210 a1rf011 sect10n. Test, ~T 862.
NACA ACR L5F27 No. Fig. 17b (b) Figure 17.- Concluded.
NACA ACR No. L5F27 Fig. l8a '\.17 c~: , ,rt~:I!l$111 i ~f if. '\- L f!:I; ' ~ :Iff ,'1 . ~.
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-wi fit " fPl flo ftJ , Cal R = 1 x 10 • Pigure 18.- Prellsure dit£erence across the gap Ileal ot a 0.2Oc plain aileron with ben1ed trailing ec1g8 au Gl IWa 651-210 airtoil lIection. Tellt, 1D~ 859.
Fi g. 18b NA CA ACR No. L5F27 l ,mer ,pt J$i tlHhl ' iiffil ±t ", ;Itt i;tHl± IW I ~'~ ~ilM 1m !tt'tl f .n W' 4LEl Itt I ~; 1+11 f , -11, +; ,;; " I ih ~, ,till!. I ;f c: r "1 )l
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~tion angle of ...... v.. Cl ' .1.~ ::f::-t=--+ -+- -!f~ ' :=-+-+-11- r.- -..., O , -0 nr ,r 't f j f I I t l "I "I I I, ~ ·l] .I t I fiJ:1t 'fr 6.
(b) R = 9 x 10 Figure 18.- Concluded.
NACA ACR No. L5F27 Fig. 19
-[;1+
Beveled Standard L.E. roughness
lW* m; J4 r$.; CO-NFfDENTIAL .:-rttOOtm.m¥!l#fi~J!mt't'T-+t4f!1- ;,Jb ~3=~JtEtl"~
Figure 19.- Lift characteristics of an NACA 651-210 airfoil section equlpped with ~ sealed-gap 0.20c plain aileron with beveled trail- ing edge. St8l1dard leading-edge roughness; R = 9 x 10 ; test, 'lDT 866.
Fig . 20 NACA ACR No. L5F2 7 F1gure 20.- H1nge-momen~ character1st10s of a sealed-gap 0.20c pla1n a1leron with beveled tra1l1ng edge on an HACA 651-210 a1rfo1l sect10n bav1ng standard lead1ng- edge roughness. R = 9 x 10 ; t e st , lO T 865.
NACA ACR No. L5Fi7 Fig. 21 , L lm - "1 ,r:! ,r+11 ·r' f~ I 'tc ' ,Jj .. ~ " t i i Jl , I ,e ,. 1ft I ~ , I¥ti~ f:~\~
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I ," >, L- ,- '- - '-- Figure 21.- Pressure dlrrerence acroaa the gap .eal or & 0.2Oc plain a11.eron with beveled trallins e~ on an HACA 651-210 alrt'oll section having standard leading- edge rougbDeas.R = 9 x 10 ; teat, 'mT 866.
F ig . 22a NACA ACR No . L5F 27 CONFIDENTIAL Ai r foil s urface R X I 06 Sm ooth -- 9 -----1 Sm o ot h ~ ~ s tandard L. E. roughne s s --- 9 8 ., ~ '" ~ '" ~ ~ 0
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Figure 22. - Variation of aerodynamic characteristics with aileron deflection at a constant section lift coefficient of 0 .20 for an NACA 651 - 210 airfoil section equipped with three interchange- able s ~ai e d - ga p 0 .20c plain aileron s of different con tour .
NACA ACR No. L5F27 Fig. 22b CONFI DE NTIAL R Airfo11 eur1'ace 8Dooth -~ 9" 10 8Dooth ~ ----- 1 ~, ---9 Standard L.R. rougbneee .~ '" " , '" '-~
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F1gure 22.- Cont1nued.
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AC H __ T_ with equivalent change in Figure 23. - Vsriation of the hinge-moment param eter Aao/t.lJ a sectlon angle of attack requirec to maintaln a constant sectlon 11ft coefflclent of 0. 20 for deflectlon of sealed-gap 0.20c Pgaln al1erons of dlff erent contour on an NACA 651-210 airfoil section. R = 9 x 10 • Fig. 24a,b NACA ACR No. L5F27 Cb
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!lc g Variation of the h1oge~oment parameter __ T_ with equivalent change Figure 24.- Ano/AO a 10 section angle of attack required to ma!nta1o a constant section lift coefficient of 0.20 for deflection of sealed 0.20c 10ternally balanced ailerons of different contours on an RACA 651-210 airfoil section. R = 9 x 106 • NACA ACR No. L5F27 Figs. 25, 26 CONFIDENTIAL .; -=t '- a <l .; .2 <: ., ....
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L --I.- '- .- -i- - -' Jl CONFlpE~TIAT i - i ~- J, I I -i~ -< ..&. 1 I 1 i Section angle of attack, :' tto ' deg i I I T Figure 26. - Z!fect of aileron con t ~'r on the section profile-drag coefficient of a·. NACA 65l-21Cl airfoil section equipped with sealed-gap 0.20c plain 0 6