Comparison of pitching moments produced by plain flaps and by spoilers and some aerodynamic characteristics of an NACA 2...

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Material Information

Title:
Comparison of pitching moments produced by plain flaps and by spoilers and some aerodynamic characteristics of an NACA 23012 airfoil with various types of aileron
Alternate Title:
NACA wartime reports
Physical Description:
10, 6 p. : ill. ; 28 cm.
Language:
English
Creator:
Purser, Paul E
McKinney, Elizabeth G
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:
Ailerons   ( lcsh )
Aerodynamics -- Research   ( lcsh )
Genre:
federal government publication   ( marcgt )
bibliography   ( marcgt )
technical report   ( marcgt )
non-fiction   ( marcgt )

Notes

Summary:
Summary: An analysis and comparison has been made of the pitching-moment characteristics of airfoils with plain flaps and spoilers. Aerodynamic section characteristics of an NACA 23012 airfoil having a retracted slotted flap with a plain, a slot-lip, and a retractable aileron are also presented for a large range of aileron deflections. The analysis indicated that the pitching moments produced by spoilers were less positive than those produced by plain flaps of equal effectiveness. The data from two isolated cases indicated that the pitching moments created by the spoiler increased less with Mach number than the pitching moments produced by the plain flap. The positive values of the pitching moments produced by both the plain flaps and the spoilers decreased as the devices were located nearer the airfoil leading edge.
Bibliography:
Includes bibliographic references (p. 9-10).
Statement of Responsibility:
by Paul E. Purser and Elizabeth G. McKinney.
General Note:
"Report no. L-124."
General Note:
"Originally issued April 1945 as Advance Confidential Report L5C24a."
General Note:
"Report date April 1945."
General Note:
"NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were previously held under a security status but are now unclassified. Some of these reports were not technically edited. All have been reproduced without change in order to expedite general distribution."

Record Information

Source Institution:
University of Florida
Rights Management:
All applicable rights reserved by the source institution and holding location.
Resource Identifier:
aleph - 003613134
oclc - 71201546
System ID:
AA00009379:00001


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NJAck 1-l(


ACR No. L5C2&4a


NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS






WAR 1TI ME REPORT
ORIGINALLY ISSUED
April 1945 as
Advance Confidential Report L5C24a

COMPARISON OF PITCHIG MOMENTS PORHDCED BY PLAIN FLAPS AND
BY SPOILERS AID SOME AERODYNAMIC CHARACTERISTICS
OF AN NACA 23012 AIRFOIL WITH
VARIOUS TYPES OF AILERON
By Paul E. Purser and Elizabeth G. Mc inney

Langley Memorial Aeronautical Laboratory
Langley Field, Va.


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-
,vil' ol held under a security status but are now unclassified. Some of these reports were not tech-
Saically edited. All have been reproduced without change in order to expedite general distribution.


':
.p
j.jjj .... .'


L 124


DOCUMENTS DEPARTMENT


Vr







































Digitized by ihe Iniernel Archive
in 2011 wilh funding Irom
Univeisily of Florida, George A. Snmahers Libralies wilh support from LYRASIS and Ihe Sloan Foundation































htlp: www.archive.org details cornparisonolpitcOOlang








NACA AC!R No. L5C24a

? ATITC.AL AD'''"IC CO"'IT -E ".iR A3RON;,JTICS


AF','A"C? 2 .7'IDT' ITAL '[Y


j"'M ARIST I 07 PIT '-' "..I. i. '' P .R'IY-C Y PLAII -LAP.S AND

T' STFTILI.S ^L 3 A -,.ID :!AiTC :: AF AC"TERIS IC3

OF A' P'ACA 25.012 AI'7'CIL T",UIH

'A'.PRIQTS 7' 25 i"^' ,'.ii A L C'i:

.7 Psal E. Purs r and s .li zaber.h r.c::in..ey-





An analysis arlj c:mnrisoln ha- been ri.a'i of the
niicchin6-mome-nt. characteristic el-' if irf s iL;ith plIrin
flars and sco'.ler.. Ae.-oJyn-amic secti )f c:rr-ct Lestiics
of ran :..iC.A 2.1'i2 Pirfoil having a r-trtc;.ed latte'. flap
with s rlein, slot-lup, en a r PtP'sa CtL le ?i :-): '-re
?ls. :.Pe:nt i for' lrt.e re..u e of eicl.cri d fl cl. o I s.

The analysis indicat'e- that the niE.;'in. moments
orodiucsd by s-oilers v ere less o-1 '.ive thcn those pro-
duced by plain flo-~s of eq..,l eff --:'ivncss. Th.e data
frnm two iscloted c.-ses 'i3n, -.ete' t,--t the pltchin -
monents cre;st-dri b., th s",.' I .ic.- :s- less "it.-. .:ech
numbiir ch.hn th' c-itchi:wn, .c.,nts ? -ouc3a by: the pain
f!an. The o.itivje 'l. ':s of tf"= ...i.tc-,in rLo-6nts produced
by both the plain flr-s 'r.j the soozlers uecr.:d-. .E d as
the devices were locatLe rerreo the irfoil l-'.i r.z ed.-e.


INITHC-Di': -TON


The NACA h.s undertaken a brief investigation of the
pitchln2-om.onent characteristics cea'.ue b,; vr'c-i.us l.ateral-
control aevices for sc :.licct i n to vwng-tv'ist -roblems in
high-soeed flight. Pitching-morr.ent data for olpin-fiep
controls have been publiIhe i previo'usl~Y (see r6fCI ences 1
to 5, for exa-ple) and sor. e dst-. 2r: spooil "-ty- conrtrois
hsve boen published in references 5 tc '. The effects of
tr-ilin--ed..3 mcdifi cetions on the ;.itchinrg-mon.ent
ch:n.rct-ristics of .irfoils .iith plain fl -ps hCve b:.-rn
discuss in reference 3.








2 CONI;'FID .ITIIAL rNA'A ACR .:c. L li2aa


Tests in two-direnlsion?1 flow of an rTACA 25012 airfoil
witi a laini r-ileron on i with two spoiler-tyoe Pll1rons
(a slot-io qnd 9 retractEble -ileron) were reported in
reference 9, but the pitchinr-iioment dast were not presented.
The present report gives the section j)itchinh-mornent
cnerEcteristicz en:1a other section data for these three
9ri'rPnemnents. A brief nrFlysis is also included of various
dite on the oitching-,r.onent ch -ractei-itics of airfoils
with r.lsin fircs and with sooiler-s.


COEFF'IIENrT3 AND SYMBOLS


The coefficients xnd the symbols used herein are
defined as follows:

C7 airfoil section lift coefficient (L/qc)

Cjo airfoil section profile-drag coefficient (do/qc)

c airf'il section pitcaiin.-moiicr.ent coefficient about
quarter-chord port of oirfoil (m/qcF)

cha .ilerorn section L:inr--n.oi';nt coefficient (hg/qca2)

where

I airfoil secticr lift

do sirfo.l s-ctjon cr.-.file jira

m eirfoil section itching moment about quarter-
chord ooint

ha aileor, s.ctieil hin.e mioment
1/ 2"
q d:rnmiric pressure f pV j

c chord of bPsic airfoil with flap neutral

Ca chori of eileron


CO FIDENTIAL










IIA'2A ACR No. L5GC2a C lFIDEITIAL 5


7 velocity of frs. stre,0.i

p raszs density of air



a rngle c.f stt c' fo r r :rf f: f ir-finite E -e ect
r.R-io, i-3 re s

6a a 1 ~l ron dee lectcor, dCre "gre, :_sitive when
tra il in ed-c- r.ove:" dlot

6f slotted-fi a,. defilecti on, de'res positive 'Ahen
tr ii inc' edTe moves ud ,,'vn

cs chord of s oi.le:' or rz tract bl aile!'on

Ps rejectionon frrm .irfo l surface of sooiler or
ret ra ct.ab- e ai leo-- on

x ldistPnce frorr srfcil lea;.i;r edge to flan hinge
line or tc outer edge of sc:iiler

rat oi' change of' itcl:in -.i.cn.nt coefficijnt vith
vo6 cL control deflection .t coinstentf life

'-- r.-r-te ofr cheir..-e of nf zl., of sttacK,, .ith control
\ /c d3flection --t ccn s .r:t lift

E ) r te of c-ninge of ni t..i.n:-: r omrre. t coefficient
\ ocv with efficti',! n- n _- of L tt ck at cons t rnt lift



( mo/'0)cj

:T P,!ach number (V/a)

-. vlocity of sound in free strmrr.


CONFIDENTIAL








NCACA AC?, I-o. L '_JL.a


Ai'PA ATUJS, 7IODEL, AND TESTS


The anparetus, model, rind tests are described in
reference 9. In brief, the 5- by 7-foot model was built
to the r:ACA 25012 airfoil profile End, vhen r:.ounted in
the Langley 7- by 30-foot tunnel (described in -eference 5),
completely splrnnea th3 test section. The tests '.ere made
at a d;nsmic pressure of 16.37 pounds ;Per square fcot,
which ccrresponds to a velocity of a-out S3O iles per hour
and to a t-st Reqynolds numr.er of about 2.19 x 100, based
on the chord of the bcsic airfoil. The effective Reynolds
number (for mnLximun lift cocfficiernts) vws Pbout 5.5 x lOb,
busei en a turbulence I'rctor of 1.6 for the Lengley 7- by
10-foot tunnel.

The airfoil nrofile, chQ slot ani frlp di.reinsions,
and the sr-.rnrements of the inain-r'l and spoiler-type
ailerons arse giver, in fiauri 1. The chords of the plain
a:d slot-lin pil::roens and th- chord of the retrecteble
afj.aron in its most e:xtdnded r.csticn were 10 percent of
tie c.sjc -irfoil chord. Thi slottd-i"l&o instpllrtion
wr-s that d-sii:nt .a 2-h in rsfer'nce 5. All testO reported
her.-.n ..er. i,:ed- with the slottsl flrj retracted (6f = 00).


I'ETHODS DF AIN ALYSIS


The r.rimiir,; rI.eroduynr:ic factor conLributinq to wing
twist -ourinii rollinc- .in hi;ih-sreed fli;ht is the p; thing
moment produced by tr.e l.telr 1l-control device. For normal
win.3 and i1 lecrons, the pitching Iocn.ent -roduced by
sileron deflection twists the wing in such a way that the
lift induced by the twi't o--'os. the lift inuuced by the
aileron deflection in-l thus effectively reduces the lateral
control evailrbl".. Thz pitchln.r :'io'. nt (or the wing twist)
produc--d by a gi- en silron deflect-on incrc-ses approx-
imnitely ts the square of the spo-ed snd ?t some point thu
lift induced by the wing twist bil.r!-ces tih lift induced
by th.e a1:ron .deflection and th- rir*jline does not roll
when the Eil-rons pr.- .eflectud. The spo d at which the
literal control becomes ;.zeo is -kno-wn as the reversal
speed,

In or-ie to judge the rtlltive merits of various
latersl-ccntrol devices vith respect to wing twist, the
pitchin,.-rmoT.nt cherecteristics must be compared on the


CGON FIDENT IAL


CCNFIDZFTIAL








I'ACA ACR ;!o. L5C24a C T!FIDDITIAI


.Jsis of equal effectivenes:-. The pitcl.ing-,.:oment
prpri-meter used sLould crierefore be blse. on the carn.-e
in rolling :ior.ent, lift, cr effective angle of attnct.
produced by the aileron rather thLn on the aileron

deflection or spoiler .rojection. The slope ( )

was t he 'ef Ue used to cComarS sll the '-:lsin fle;a sn Jn
spoil ers orn an equPl-ef'rctiveness O sis, since t.lis
.erD-rmeter- indicates trn c:-anr,.e a ia, pit hinr -iol.:..enc coef-
ficient rs lting fro! iUL-it chl'.r e in the effective
angle of attack of the norticn o- tht wii-FT covered by the
ai ic ron.
The slone of the 1itchi;n-molent-coefficient curve
w,? t-k'en at const rnt lift (c, '".1) because, whern the
airr-laine is rolledl by the s;F i. 1Trn, the aileron section
of the j.,jn? operates at r.e :-;:. c rist.nt lift. Although
s-oi icr-typ-e FileR'onrs, since theiy are ',xed c'- only cne
wing at n t nie, o'er-'tu frchimr fromC c;...oito..s of constant
lift thar. the 1asin-flaFp i :lr'ors, the r'rR:c itenr at
c nstanlt lift is s.ill believe.: I; 'ce :.orIe ,irrly rr; --
senr!tativ-_ of actuil conditions th'a- a ep rE' .vttr at co-mns trnt
an.le of att.ck. /
A logical Raciss ir einst which tj plot --
C -o \p-1 a lo/c r
for pilirn floEs vould )e- the fl.lp ciord but, rhein spoiler
dati must also 'e :resented on P c-: psar-ble basic, such
ai- abcisse is no 1.or.er loCcril because spoil1er chord
(or croection) iU n.;lo;,ou3 to i'i?;: declctior rsher
thar to flen clord. ThJe dsco were therefore plotLed
arsinst the chord'wi:se Iccation of the ?.Iein-flls! iirie
line oL of th.- outer edge of thre jpciler. Por devices
such as the slot-lip eilerons, which were considered to
be sp:'ilers, the location used was tha ,ve-rae location
of the aileron trailing edce ever the deflectic.io rrnge
considered.

All the finite-span dat? (reference 5 and 6) were
converted to section cherscteristics by use of refer-
ences 10 pnd 1]. The values of s7.ect ratio used with
the charts of reference 10 in computing section character-
istics frc.r. the data of refer.znce o were corrected for !'.ach
number effects by the method of reference 12. At each
value o' Miach number, the ge-.metric aspect r rtio was
multiplied by the factor .*,. !2. Thii procedure gives
an effective reduction in ea-,ect ratio as the raicn number
is inc-eased.


COr'F IDEZT I AL








COFTLE:D2'!l 1'ACA ACER 'o. L5C24a


RES.1 '"S AC' MD DT 3C 3i.


Test art .- The Perodr iFnir s !c::ion chperecterisc,.cs
of m. I:AC A 27.0: sir'fo1' nvin7 a retrEctod s .tted flap
'with r p-iri, a slo-ilio, rad a retr-,ctable .ile on 8re
'.r-eseted 'in figure 2. Phe lift ani -reg (or roii,-
mLoment &nJJ yS insr-mo:..er.t) ch-r. cterlstics rid t'.e hinge-
n.cm.ent ch r- cte. stics have been em ..1' discussed in refer-
ence "'he i tchil:-n.orannc date rr.sented in figure 2,
togetbhr ,aith tt1.er rjublished ana unpu.clished data for
[Vsch rLcr.bers u.) to ?bout 0.5,. have beer, sumrmerized and are
pre3erntted In figure .

Pitchlntg moments :rDuced by pl-in rfios.- The
e:.:ne.-i~' ntl d sr on th.e .iltc-hi... n.ijr.o rts produced by
plpin flans sEr,:vr, iin fiar 3 aree very we, l with values
co.rinuted from 3G'ueart's Lhir-e, 'foil theory (references 1
and 2) boa- in r:Srnitulde Ad in variati.cn "rth x/c.
These date i-. i L t.e that, for r 3iual c'hr: .e- in effective.
'a-l of Rtt.ac equall rollinL momrrnt ) wide-c ,or-d f aps
produced nsi', l .L:,'- pitci-itrf r-otruin tna-n r.er'e.v.-g.n rJd fla's
, 3, cc ns.-quar: ly, that tr:; us.- of wilde-ch'ord fP'ivs would
io lo: t tt 5 tt? nriien i of i !.;.!"h r v'i uei of t'1- r.--v S' l
s ecd. The use of wiLa-chord ipr.s however, wi-.l bs
lirritLd by whether t.-ier i.r.e mor.'icents can be well enough
'alenced to producee r'epsonabil values of su~ ck force.

It s'-ould be nr tc- thAt thnj d-st of reference
indi2nte cth-rt tth critchiri mornrnts .r.oduced by olain
f .i es ms :/ i c,-duc-ed b:' iicr re pas top tno ei,,le b-twe3n the
uoc.r': r pnd lower sur-fsc-=s of the falap ,t tnct traling edge.

Pitchir.' mornen ts e.,roduced by sooilers.- T'he
exoerim.;nT-Tstt on th l -t nin: moments orcducud by
s, oilers frr. a relat ivu ly in.-.o th cur-v (fig. 5) and
indicate th&t, for equi -effectiv=ness, thb spo'oler
locatAd nearest ti\ airj'oil lma3min eadpe producess the
smallest cositiv= values of ';i a oo'er
[-,--- V iLth a Looiier
located ehi;d of about 0.-;5c, the wing twist right
augmE-.nt ratlhr then rA=duce the rol.in.g effectiveness.
The us6 of spoilers located so n-ar tho s:irfoil leading
edEs, however, is not rec:rmended since n.eny :,ravious
wird-tunrel and flight investi--tions hIves indicated that
the t;nraencius toward 1-.- .and crrctic Pction incr Ese as
the sooil-r is )lecead n-earr- the :irfoil leading edge.

C-O;:IDENTI AL









FACLn .CR I'o. L5C24a


The lcatlions of the so-iler irstqllations found acceptable
have vried from about 0.oOc to Sabut 0.05c.

Co-.orrisor.n f 'itchinF moments J.roduced by6 olain fl ps
and spoilers.- The deta presented in figure indicate
Thaet ne iitchinz moments produced by niin laps and
sooilers have about Equnl varirtionri with fla' or cociler
chordwi-se location ari- tht ti.e values of (cm are

less positive for the sonilors than for the 7- lain flans.
'/Wrin s con;?. :e.ion is mr:de at chcrdwise locationre ..rmaliy
ised th- t is, 0.7 c to 0.75c fo" s:. ojle.rs ar.d 0.?0c to
0.05c for rlair, fl,-Es, the ;itchinrI moments ni;oduceo by
sooilers are rbout one-half or ie-s of' the pitchilrnr
mornents reducedd ol airn fl.ns cf the same effectiveies.7.

",ach numz:ber effects.- Data on the effects of Mach
number op the" tuhir moments produced by cortrol
surfaces ere reltlvely scarce. co.T. prison is ,resented
in figure 4, ho.-Av.:r, of the effects of l,.aci r.umrbel' ozn
the oitchin. n:oni-nLs produced by a spoiler alieron on the
winr of reference o and on tne pitchiI- mcrnents produced
by a plain flap on an I;ACA 6b,1-115 airfoil tested in the
LsEnley 3-foot high-soiJed tunnel. The ti thing moments
produced by the -lvin flap, in ad:lition to being icar3r
than those produced by the spoiler, also increase with
Mach number at a rate greater tha,. tnas indicated by tho
1
Glauert-Prandtl factor The pitching moments
Vi I2
produced by the snoj ler, however, increase at a rate
slightly less than that indicated by -- over
S /'1 M2
most of the .'ach nuLnber range tested. Although the data
shown in figure 4 ~r-3 not strictly coiinarablt and are
for two isolated CPsas, there appears to be a possibility
that Mcch number effects r.-y be si-mller on -:itcning
moments produced by sooileis than on --itching moments
oroducId by clsa flaps.



CONCLUSIONS


An analysis of data on the Aitching-morm-nt character-
istics of airfoils with vlain fla)s and sooilers indicated
the following conclusions:


CON FIDENTI AL


CC.::F'ITDE1'TI AL









F.T,,Ai ACR No. L5C4a


1. The oitchine romrn-nts produced by spoilers were
less positive than those producedd oy rain flaos of equal
effectiveness.

2. The positive values of the --itci:ing n moments
nrodjced by both the plain flaoE and the spoilers decreased
rs the devices were located nearer the airfoil leading edge.

5. The date from two isolated cases indicated that
an increase in Iech number caused less increase in the
pitching moments produced by tne spoiler then in those
produced by the plain flao.


Langley Meemorial Aeronautical L- bor-.try
National Advisory Ccmmittee for Aeronutics
Lng ley Fiela, V?.






























S


CCNFIDE TI AL


CO'IT DET TIAI








itACn ;XCR I0o. L.C2ka


REFERENCES


1. nimes, Milton B., Jr., end Sears, Richo d I.: Dater-
mination of Control-Surface Characteristics from
NACA Plsin-Fias and Tab Data. !IACA Re:. Io. 721,
194-1.

2. Osiuert, H.: Theoretical Reietionships for an
Aerofoil with Hinged Flan. R. & M. No. 1095,
British A.R.C., 1927.

2. Wenzinger, Carl J., and Harris, Thomas A.: Wind-
Tunnel IrvestlFation of an I!.A.C.A. 25012 Airfoil
with Ve-rious Arran.-ements of slotted Flaps.
ACA Re: N!. 6b4, 195;.

4. Purseo, Paul E., and Ri2be, Johln iv.: Wind-Tunel1
Investicrtion of Control-Surface Characteristics.
XV Various Contour modifications of a 0.'0-
Airfcil-Chord ipin Flaa on an !PACA b6(215)-014
Airfoil. NACA ACR Ho. 7L20, 19Li.

5. Purser, Paul E., Fand Turner, T:.-mes R. : ; -ina-Tunnel
Inv:stiuction of ?orforated Split Flaps for Use
as Diva Brazes on a RectLanjulsr NACA 25012 Airfoil.
MACA ACR, July 1941.

6. Leitone, Edr:urnd V.: An Investi-7tion of t:he HiEh-
Sneea Lateral-Control Characteristics of a Soiler.
MnAC A A' lic. 4C27, 1944.

7. Shortsl, J. A.: Effect of R3tracteble-o:.-iler
Location on Rollir.n- and Y owi nr-IMoment Cocfficients.
?ACA TN N!o. 4199, 104.

8. Pursar, Paul E. and Johnson, HSrold S.: Effects of
Trail in--Edg-e [ JificatLons on Pitchin-;..omrrnt
Charvct.ristics of irf.:ils. "nC, CB No. L4I50,
1944.
9. Vvenzinger, Carl J., and BEmber, .iillard J.: 'ind-
Tunnel Tests of Tnree Late-rl-Control Devices in
Combination with a Full-Span Slotted Flep on an
,.A.C.s. 25012 ,drfoil. N,,C TN No. b59, 1958


COiNFIDENT I,


CONFIDE i r Tl








HACA ACR 'co. L5C21 a


I /
10. 'Veick, Fred E., and Jones, Robert T.: Resume and
Analysis .f I.A.C.A. Lateral Control Research.
i :C A rep. Ilo. 605, 1937.

11. Pearson, Henry A., and Anderson, Raymond F.:
Calculation of the Aerodynamic Characteristics of
Tapered ~'ings with Partial-Span Flaps. !IACA Rep.
No. 665, 1959.

12. Goldstein, 3., and Young, A. D.: The Linear
FercurbAtion Theory of Con,-pre.3sible Flo;', with
Applications to Wind-Tunnel Interference.
R. & M. No. 1909, British tA.R.C., 1945.


CONPID ITIAL


CONFIDENTIAL






NACA ACR No. L5C24a


CONFIDENTIAL


P/ain aileron


Slo-lip aileron


L-ocus of oileron
upper qnd lower
edges


Retractable aileron


CONFIDENTIAL


oNATI FO AUWISO
COMMITTEE FOR AERONAUTICS


Figure /.- The NACA 30/2 OI rfoi/ with various
types of o//eron and with a plotted flop.


Fig. 1







NACA ACR No. L5C24a


CONFIDENTIAL


o so
S.08

S.04


. 0

^ ^ -.04
,,






.16






2.0

*-, 1.6


.Z.O
s..




.' "


1 ^
o




0
4 l
./ r


Ang/e of attack, ao,deg
(a) Plain ai/eron; c=Ol/Oc.
Figure 2 .-Aerodynmi/c section charac/er/s/ics
of /VACA 23012 airfoi/ with various types of
aileron. 6f=0. CONFIDENTIAL
*


Fig. 2a






NACA ACR No. L5C24a


CONFIDENTIAL


3.





RK













"
'-'3


.8 *




0 .8 o








1







c5o


0 o
o a


Ang/e of afac/h co deq


(b/ S/ot-//p c//eron7 cCa= ./Oc.
Figure 2.-Continued


CONFIDENTIAL


Fig. 2b





NACA ACR No. L5C24a


1
o ^












o
o
x

$






S'3
I
a






Ei o


.. IJATIIML 0SO
4 IMM I FOF AEROA I N AtmC


1 I I I


0a r2


s Ps
(percent chord)
0 0
A 3.33 3.33
O 3.33 5.18
S3.33 6.86
S6.67 6.67'
> 6.67 /0.09
< /000/ 10.00


lo 2U


Angle of a//ack, ac deg

(c) Relracfab/e aileron.
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