Wind-tunnel investigation of control-surface characteristics

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Material Information

Title:
Wind-tunnel investigation of control-surface characteristics
Alternate Title:
NACA wartime reports
Physical Description:
18, 36 p. : ill. ; 28 cm.
Language:
English
Creator:
Riebe, John M
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:
Airplanes -- Wings -- Testing   ( lcsh )
Flaps (Airplanes)   ( lcsh )
Aeronautics -- Research   ( lcsh )
Genre:
federal government publication   ( marcgt )
bibliography   ( marcgt )
technical report   ( marcgt )
non-fiction   ( marcgt )

Notes

Summary:
Summary: Blunt-nose and elliptical-nose overhangs of 0.35 and 0.50 flap chord and a plain overhang on a flap having a chord of 0.20 airfoil chord have been tested in two-dimensional flow on an NACA 0009 airfoil. The results of the tests are presented as aerodynamic section characteristics for several flap deflections with the gap at the flap nose sealed or unsealed. Tests were made also to determine the effectiveness of a tab of 0.20 flap chord on the plain sealed flap and on a sealed flap having an elliptical overhang of 0.35 flap chord. The pressure difference across the flap seal was also determined for the plain sealed flap.
Bibliography:
Includes bibliographic references (p. 14).
Statement of Responsibility:
by John M. Riebe and Elizabeth G. McKinney.
General Note:
"Report no. L-196."
General Note:
"Originally issued June 1945 as Advance Restricted Report L5F06."
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 - 003804691
oclc - 123895139
System ID:
AA00009381:00001


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Full Text

' L-/
- ..


ARR No. L5FO6


NATIONAL ADVISORY COMi
ua







ORIGINALLY
June 191
Advance Restricte

~ WVIND-TUNNEL INVESTIGATION OF CC


MITTEE FOR AERONAUTICS


REPORT


ISSUED
S5 as
id Report L5F06


)ITROL-SURFACE CHARACTERISTICS


XXII MEDIUM AND LARGE AERODYNAMIC BALANCES OF TWO NOSE SHAPES

AND A PLAIN OVERHANG USED WITH A 0.20-AIRFOIL-CHORD FLAP

ON AN NACA 0009 AIRFOIL

By John M. Riebe and Elizabeth G. McKinney


Langley Memorial Aeronautical
Langley Field, Va.


Laboratory


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. Some of these reports were not tech-
nically edited. All have been reproduced without change in order to expedite general distribution.


L 196


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*TACA AR7. No. L "O

:ATTIOTAL ADVISi0Y7 COTITTE FO? AERO''NT:ITCS


A'-- A:'E F FCTD-' T C


WIND-'T-i:::L .IE:VE3TC-ATICI' 3Fp CO'?LC'L-SURFC- CH.ACTR' -. .TI .S

XXII ::EDIU.' a'D L':. ,ORDY!A'.TC B.tL7_'CES CF ?VO .'"E: S.i'LS

AnD A PA:: OVERHANG USED ..IT 0. .0-.I:ICIL-C: CRD FLAP

C'I A: ::;ACA 009 '.VCITL

SJo JI .:. -it.e and Eizaciethi G. "cKinr.ey





Plurt-nose anr li.* t S1-roe cver.'rws of 0.35
and C,.5f, llan ch r.i anC. a [. -:"- ,: :.'. on a flap
havi:'mr a cholrd of 0'.' airf3 il chr:i have been tested
in tv'o- .:ne:, '.al fl-w .r. ar. n ..CA C:9 airfoil. The
results of ti t-: :t .-r- -,rercnt .e *E aeroC yr, a."-c
section sc.'.eracterisA.?s for ce 1 fai .pn deflections
with the re, .--- fl-? r. .e :.:D ._r, unsealed.
Tests ':ere r; '-e 1a-, t, .:,ter-ir.e t!rt: err ff-e.- til 'en:ess of
a tl.. 1 CI-c .. "- n e 'f'1 a '"
& ta :f C.. !< chr'd on .he lA.ir.. seale.i "fla -.d
on a setle fl, p h.a-:inr- n el.- ctical o-'erha:-.1- f- 0.'5
flap h-crd. Le prcs' ..:r.' c.iffIer.e',:ce across t'he fl-
seal e as als) cetc .: :Ee for !-"e rl'ir sealed flap.

The res .Its irI:' a e t ',t t-:'e flain sealE'. flap
haK. th-e lr..-rest lift-cj.r-re -lo,< e, '"- --r-eas the slopE.
for the u.53-i'lar-ch'-?rd -ver:.':i- .:F:ere the same as or
slirhtl larger t'- ar. or the O.u-- lap-cfrC'; overbi'tr.r..
A red.uctior in cl 'e ca rsed o ,.ir. C-c ..:. the f'l p c ap
increased ti th 'calance :l,.:r..

The cr.anr.e 5r. ift -coIff t r';.- .iti. flap dci sectionn
generally increcas.er vh-ln :..e 1 a;- C sealed -r when t:h
balan re nose sh:ae '..s 'cLa.r:- e r:. ae lliptical to blunt.

Salilr.. the iflay. -e ersill:- e the variation
of flap hi r. e-r.c.".e:.t cIc; icler.t .Ltith .n .le of attack
and with flap deflecti or. r- r.e n.ativ';-. Chan.,rnin the
no-e shape fror. bl'nt ': elliptical :.tleC the variation
of the fl:.p l ir.-e-.._r'e,:r c.,:f. i, le t '.ith anr.;Je of
attack :,ore negative ::,r the ceald r. .rj. more positive









2 NACA ARR ilo. L5F06"


for the unsealed .rap. At small flap deflections, the
variation of flap hinge-2[oment coefficient with flap
deflection was more negative for the elliptical-nose
than for the blunt-nose 'lap; at large deflections,
however, this variation was more negative for the blunt-
nose flf p.

The change of flap hinge-moment coeffici nt with
flap deflection for the unsealed blunt-nose overhang
had a larger variation with balance chord than the
change of flap hinge-moment coefficient with angle of
attack; for the sealed blunt-nose overhang, these vari-
ations were about the same in the range of balance chord
from 0.35 to 0.50 fla? cord. For the sealed and unsealed
elliptical-nose overhangs, the change of flap hinge-
moment coefficient with angle of attack had a larger vari-
ation than the cl.arTe of flap hinge-moment coefficient
with flap deflection.


I:TRRC 3DUCTT N


The TACA is corcuct.'ng an extensive investigation
to determine the characteristics )f various t:yes of flap
arrangement suitable for use as control surfaces and to
provide data for design purposes. The investigation,
which was made in the Lanc.ley 4- by 6-foot vertical tunnel,
has included tests of modification,- of flap profile,
trailing-edge ang.le, gap size, flay nose shape, and balance
chord; m':c.evor, most of these tests have been nad'e in
two-dimensional flow with a fl2s havin>- 2a chord 30 percent
of the a.rfoil chord (O.2Oc). Tne preser.t tests hasc
extended the inve-tigation of balance -hord anrd flap nose
shape, which was reu;orted in reference 3. for a 0,40c flap,
to a 0.20c flap. Data on the pr.srure acr-o3 the flap
noce seal anr.I a method of applying thesPe rer-ure data in
the design of internal balances are presented. Tab datP
are presented for the plain flap and for a flap with
aercdvr.-:i.ic balance.


SY3 'LS

The coefficients and s:,mbols used, in this paper
are ~df:ne' as follows,


airfoil section lift coefficient (l/qc)







IJACA ARR ~o. r5;-'C06


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

Cm airfoil section pitchirin-moment coeffi-
cient (m/qc2)

Ch flap section hinge-moment coefficient (hf/qc 2

cht tab section hinge-moment coefficient ( i/qot2)

PR resultant pressure coefficient (PL PU

where

I airfoil section lift

do airfoil section Irofile drag

m airfoil section pitching moment about quarter-
chord point of airn'oil; positive moment
m),.rve no-e ,of airfoil up

hf flap -cctiln hire mon.ent about flap hinge
axis; positive moment moves trailing edge
down

ht tab section hinge moment about tab hinge axis;
positive moment moves trailing ede- down

c chord of basic airfoil with flap and tab neutral

cf flap chord from flap hinge axis to trailing edge

ct tab chord from tab hinge axis to trailing edge

q free-stream dynamic pressure

PL static pressure on lower surface of seal

PU static pressure on upper surface of seal
and

cb balance chord

ao angle of attack for airfAil of infinite aspect
ratio; positive when no::e of airfoil moves up







HACA A:iR :!o. 5F06


6f flap deflection with respect to airfoil; positive
when trailing edge is deflected down
6t tab deflection with respect to flap; positive
'.,hen trailing epdg is deflected cdwn


chf
a = (6 6
C7, =.) ,6- osf



(' t

c 6f = (f-c ,
6f

Chfa "
S/ f, 6t


Chfft f J


h ft \4/o,






-Q 0, 6t


The rubccripts outsidee the parentheses represent the
factors held contaYnt .,iurng -Ye rmea.urr~.ent of the
parameters.







I.ACA ARR No. LS'06 5


APPARATUS Ai'D I:CDEL


The tests were made in the Langley I- by G-foot
vertical tunnel described in reference 2 and modified
as de-cribcd in reference 5.

The model, "hen mounted in the tunnel, com7l. tc.ly
spanned the test section eyciot for ---inch clearance
3%
gaps between the m)dcl and the tunnel walls. '.'ith this
type of installation, two-d]:r;nional flowI is closely
approximated and the (r.ctj.,on characttrit tics of tho
airfoil, flap, and tab may determ-incd. Thi riodel
was attached to the balance frame b torque tubes that
extended throi'gh- the "idc.: of ti.ei tunnel. The angle of
attack war set frorn ol.tsi:'et the tunnel by r.:tatin:. the
torque tubes '.'.".th a;in clel ri drive. Flap deflections were
set y o.n elecLrical position i.,i:ator, and tab del lec-
tions were set by a te!r;:plct. Tlhe nnlre nienLt of the
flap v'ero inea-ured witth a ..ecal torqlie-rod r.alance
built into thie i.iduJl.

Tab, hj.incie m.:meiitr. '.:i..rc mciaz ur-:d by an ,1"ectrical
strain ga..e ins tall. d. in the r i-d .l. .For test of the
plain sealed fl..p, the nrrerior difference across the
gap seal was measured on a ,anoie-eter.

The nimoel (fig,. 1), vl-ich 1bad 'a c.na.rd of 2 feet
and a span of 4 feFt, was mnadd of lar.:iid.ted i..:ihogany
(except for a steel tab), was Pcro'dvynDlmiirally sro'otlh,
and conformed to the I1ACA 000' profile (table I). It
was equipped wnith a 0.2 c fla-: and a C.2Ocf plain r,.b.
The flap had a plain r.~on vlwth a radius tlhat w'-as ap;.roXi-
mately on-half th airfoil the aicfnic:?s -it the flap hinge
axis or war fitted with O.35cf or 0.50cf bliunt-nose or
elliptical-noce ae:'dynamic bal ances. The elliptical
nose, the or.dinate:- c '.a --.ich a'*re ,iK'.ern n tvbli II, was
a true (llips e tan.,ent t;- the airfAil coLtoiur at the
flap hin'e a::xic. The radii svo.n f-.urec 1 determined
the blunt and i lain r-inoses.

The varli~ur. nose bloC,- we',rc inr.tc: ir. ianr-eable and
were fastened to the flan at the *,nge: a:-:e. In -r-dcr
to keep the -ap at thc f'.ap n-'e at O.C0'1.c, blocks
corrcspo:iidinC to each b.al]ance cr .rc t. v'. att..tchcd to
the airfoil j:~-t a "_Es d of the-- hal'iranc For L'C Tb e',lcd-
gap tests, airtight. fabric ';.a f::tcn-d t atrecn th flap
nose and th. airfoil.







NACA ARR No. L5F05,


The 0.20cf tab had a nose radiu. approximately
one-half the airfoil thickness at the tub hinge axis.
The tab gap was 0.OOlc for all the tests.


TESTS


A dynamic pressure of 15 pounds oer square foot,
which corresponds to a velocity of about 76 miles per
hour at standard sea-level conditions, was used throughout
the tqsts. The test Reenolds number was 1,430,000 and
the effective r;eyn-lds number was approximately 2,760,000.
(Effective Re'ynolds number = Test Reynilds number x
Turbulence factor. The turbulence factor for the Langley
4- by 6-foot vertical tunr.el is 1.93.) The 'Tach number
for the tests was about 0.10.

The riayxi um error in anrle of attack appears to
be +t0.'. It is estimated that the flip and tab deflec-
tions were set within 0.20.

An experimentally determ::ined tunnel correction was
applied to the lift coefficient. In acc:orda-ice with a
theoretically derived analysis similar to that presented
in reference 4 for finite-s,~rn models, the angle of attack
and the hinge-mo.ent coefficient were corrected for the
effect of str-.amlir.e curvature induced by the tunnel
walls. The increments of drar coeffici~nt are believed
to be reasonably tndependert of tunnel effect, although
the absolute value is suYbject to an unknown correction.
Inaccuracies in urorel construction and assenbly of inter-
chargeable blocks probably caused the sn.mll flap hinge
moment at ao = 00 and 6f = 0.

A suTrma-y of information for convenience in locating
the data for the various model configurations is presented
in table III.


HC'ULTS ALD DIS'UJSIOII

Lift


The lift-coefficient curves for the plan flap and
for th, flaps with various overhancgs :;rer given in figures 2








i;ACA A"R io. L5.F06


to 11 for the flap Ea1T- both: sealed a.la un.-Cealed. These
curves v.ere ronli ear at l'tIge fpic deflections. The
flaps with elliptical-nose overh:m-: s generally developed
lift to larger flap d,:fleetions than th.: e vith bL]nt-
nom"; ?ierhangs.

Parameter values jbta.ined fromn fiureic 2 to 11 are
surLr arized in table I". Tih variations with ba-.ice
chord -.f the lift. ar:r~eters c? C, c and o6, are
riven in firure 12'.

With tl-e -aFs si'.'.l. d and ,un- ail.ed, th.-e lain flap:
had the largest ,:alue.r of the slope 3.' the lift curve CL,
whercas the '.alu.t p jf c0 for the O.OcCf overhar.gs
i.ere the s 'rre as, .:r lr er' tl.an .or tlie 0..' ver.ang .
This variation '.as s .i 1 ir for the C.- Cc flap (refer.-ncee 1)
A reduction in c ceu '-, t r. 't l r-n the -ar i created
Jwith balance chrd.

The value 'f c. .a: u.;.nl la.-r-er for the blunt
than for the ellI.ptica'l r.7e. ::-ce:.t for the flap with
the O.EGcf blun';it-r:,s;e overi rinz, -& cll r., the gap ince -ased


The flap 1 .I't effectl-:er.n .- cr .....a eter a.,.. .decreased
as the ba- la .ce cI'ord ri-2:-eei ed, c ::E.'t, for the la:p v'th
the 1'n.C'-:i led bl'..nt-.n:-e :.verh- n., ar: a as usually l-ar,-:er
for tried l'.unt-nore tLrn or the ell .ptical-nose cverhsnr.
Seali I. the ap, increy.-7d cf for t1.,t elliptical-n're
ovferh.anc and tlhe plain flare but tE:-;' rally decreased it
for the 'c lnt-nore :-,vcrh an The ,,alles of ag, given n
in tab-le IV. andI figure 12 vcre r'e' :' s 'r-. c over a small
flap deflection rar.rc at c 0 air'. therefore are nirInly
useful as a comparison1- of t e vcri-iut- cionfir ur.Ltions tested.


:inr-e Mitent

The curves of "fl;n- '-iire-i- -e. nt- ,coefficient as a
function on anrTl of tticl. at c.-,7r .-"t fl.sp deflections
are Fpre e:ited in figures to 12 for the plain flap and for
the flap:- with "arious overhan7r hj appreciable flap
oscillations werere '-i. c 'ed t r-u ih;, h:t the lap deflection
ranre testred, ailtboui-h :h -r :cilli'i: ns occurred on
the 0.40c flap (refcience 1).








!TACA AHP. No. L5FO'.


The hinie-mnement paramreters Chf
_h .fa


ard Chff


presented in table IV and plotted against balance chord
in figur- 13 indicate that the O.Ocf blunt-nose over-
hanr was overbalanced (chf was positive and had a

positive chf, for the Cap sealed and urqealed. (Values
I 0f


of Chfa
and values


were determined at ao = 00 and at 6f = CO
of chf were determined at a. = 00 and
I f 0


small flap deflections.) The 0.'120 flap was found to
be overbalanced for conditions si.iler to tho-e for
which the 0.40c flap tested on the same airfoil
(reference 1) had been overbalanced. FDr the flap with
the O.5Jcf overhang, Chff could be made negative by
the use of a tab deflected in the same direction as the
flap.

The 0.50cf elliptical-nose overhang, with :ealed
ar: unsealed IIp, hadu a r.o.itive Chf at 6f = 0 ;
at lar.-e fls deflections, however, -an -ncrease in
angle of attack or flap deflection generally -ave a
ne-ative increment of 'h-l.re-moment coefficient (figs. 10
and 11). For the O.50cf blunt-nose overhnang, flap
deflections up to approximately 150 g.ve positive incre-
ments of hInge-moment coefficient; chan'ring the flap to
larger deflectiors --ave negative increments.

Figure 13 indicates that, for the uin-.alt ed tlunt-
nose o;oerhbnr.-, chff had a larger variation with


balance chord than chfa; for the sealed .:lunt-nose
r^* a'


overhang, the variations of ch. and c. were abo

the same in the range of balance ch)rd froTr 0.ZcCf
to 0.50cf. For the sealed and unsealed elliptical-nose
overhangs, Ci. had a larger variation than chf.
ni af


ut


Chanrirn the nose shape fr-r, blurt to elliptical
m&ae Cha more negative for the e- led gap and more
^ba
positive for the unsealed Cap. Chanirng the nose shape
from blunt to elliiot.cal alco ade cL rrmore r.erative

at small flap deflections and less negative at large flap
deflections.







HACA ARR Io. L5706


Sealing the gap at the flap nose generally made Chff
and chf. nore negative. J4

Since the aspect-ratio corr-ctlons for strc:arllne
ciirvature -re always positive (reference 5) and since the
hinge-mr-ment parameters are very sriall and the sin-s are
critical f-r several of thi- flaps '.*litUi ov.-rbangs, the
slopc-s ir.may change frorn ne-ative to positive and produce
an overbalantced flap on a finite-span wing.

Pecau-e tio hinige-m7:.mntl parameters r rwn in table I'
represent the -'lopr o:'f the cur.res at 6f = 0" and a =00,
these parai.;ter.7 sh-u7?d be u-sed mai-ny as an indicaticn of
the relative erinrrts ,of thie different flap nose sFaps:. .
Because the ti:au.lated slp.s '.re valid fTr only a small
range, thel cur:e'.'s c'f linrie-rm*..et coefficient should be
used, rat!.r t.ih:n ti-- tabulated parm .i:.ters, in the calcu-
lat.on of the characteristics of a control -nu.rface.


Pit ch;i.nr oi-.ent

Values of:' th-.e I:i tc'Li'.-moment -srrameters (cmo

and c ) are c .on in table IV and iri-,'cate the

position of th.e aerocnunamic center with respect to the 0.25c
point. When the lift was varied by changing the angle of
attack at 6f = C,A the aerodynamic center for the plain
sealed flbp wis located at the 0.,fc point; the serrod-'namic
center for th.e: balance.-d flap with sealed gap, regardless
of balance chord -r r:c-se shape, was near the 0.24c point.
The eff'Eet of i.n..n:alinrig the -IapI wvas to "i-.-e the e aerocl"r-a:-ic
center O.Clc f'-..r ar..

The centcr'-o f-lift 1- sitionsdue to flap deflections
up to approY-t...atel: 15' are given in the following" table:







10 NACA ARR To. LEF03



ICenter-of-lift position caused by flap deflection
(percent c)

;0.35cf overhang 0.50cf overhang
Gap _____
Plain I
overhang ]Blunt 'Elliptical Blunt Elliptical
nose nose nose nose

Sealed 46 45 44 44 46
0.00 c 46 44 47 43 50


This table indicates that the center-of-lift position
was the same for the plain flap whether the gap was
sealed or unsealed. The effect of airseuling the gap or
of increasing the balance chord was to move the center-
of-lift position due to flap deflection forward on the
blunt-nose and rearward on the elliptical-nose flap.
The center-of-lift position caused by flap deflection is
a function of the aspect ratio (references 5 and 6) and
moves rearv.'ard as the aspect ratio decreases.


Di l 17

Because of an undeterr.ined tunnel correction, the
measuredd values of drag cani ct 'L. coni-ir'dered absolute,
but relative values of drria arc thou "ht to be independent
of tunnel effect.

The increments of section :'rc file-drag coefficient
cause. by flap deflection are r.resented in figiire 14
for the plain fl..t and in fi'.ur. 15 I-.r the ,.icf
and 0.50cf blunt-nose overhangs.


Tab Characteri tics

.ecau-e the characteri-ti-. fh.r a ta-. on a flap
with aerodlrnsmic balance, in general, are sri-ilar to
those for a tab on a plain flap (refeire.ze.ne and 7)
and are usually rniepren.dent of flap in.re shape (refer-
ence 7), only a limited inve~ttii-ation of tab charac-
teristics has been made.








IACA AH I;,. L5FOC


T!h. aer.:,,a;na ,ic se-ction! h'iai cter tics s a function

.f angle of attack, f'r a tab ratio = 1, are
-ir'e-:enLtcd in fig'reE -. 1' nd ?1 for the plain Fr5,--Iled fl .p
ank fr. tihe 0.55 c-. 1 ealSe elliptical-nose o"'erhin;,-
re pecLi.V'e. The values of ch, for the 0.-5cf

el iptlcal-n.se overhang (fil{s. 7 rnd 17) were, in general,
t .i r a' r '?lig..tl-" less 'h .-, the values for 'ih
.la-in lac, (fi- L: an. 16). .ith the tab i1flected ir,d
vith i-:; (fi.. 1), c0-t was 0.017 and ch
t fit
was '.I for t.', 1 plain r.iald flap. The tab, in -.'-eral,
was :1z'citl:," .7r,-' effcrt',-e in prc"..:; 'c- lift on the plain
fla. t;.,an :. te fla: v'ith the O.35cf overhu:-,-. The
ofafici.'e'.e: r fcf' the t'.b in :r a,,ir.g the flip hinge moment
decr-ea..(d .'t. .. del election. A comrrarisor. of figures 3
and 1' vit fi.re 1'3 .how.JL that the tab effectiveness
genera!i 7 w.s t-;p _.-:~.e v.Ye:ther the flap was at 0 or
reflected.


F'rE'c .ire Eif.f-rr,:ce across Plain-Flap Seal

The variations ?i r-sultant pressure coefficient
acro.c-. th,: p:la':n-rfla-': rose seal with angle of attack at
constar,t "rlap diefle-t.lns is i .hown in figure 19. 'The
,chn,~-e in r'e-r. lc-..t i c.t sure coefficient with -i,rle of
attach -., .;a,: found to increase "*th fl-,p
0 1t
de f l-c ti .n.

The :'-ta of fi; G r- 19 can be ui:-.:,, with t'- e of
fijT'r7'," i L deterr:ine the flap section hinge-moment
e.e!ficient at e, t i', a.-:le of attack and flap deflec-
ti-~-,: fir a 0.)Cc fla. v.ith an internal balance on an
I .?,. 00: 9 : i.1 t:i c i be shown that

,, ..f): = Chtf + P -' (1)
vi e ro

('c -) r "ctisrn ; Ln:ir'-.::,:.rt coefficient for flap with
S IB int:,,r-ll balance








12 'C.. -. -


chf section hing--,-er-nt coefficient for plain flap
with rr -sealeJ, obtaine: .fro .i figure Z

PR resultant pressure cceffrcient, ofto'.ned from
figure 19 /


K constant, obtained from firur 20 / 2

t semithic'-ness at hinge axis

c<' balance chord plus one-.ia.f _.p with

Thl bin_-e--mo1E nt parameters ch-, ard C1h6 deter-

mined from flap hinge-cmorent coefficlieni: obtained ty
equation (1) are plotted in figure 13 for lintcrn!l ba1arces
of various chords.


C-.,cr -' ONS


Blunt-nos e and ell;'.;tical-nose ovei .a- :.f 3..-
and :I recentnt flap chord (O.5EcfP and C"..iCf) and a plain
over!i:',. on a fl-)i havirn- a chord .0 pec"ce.L i.f the air-
foil chord (0.0Oc) have been tested in two-dlnfinsicrial
flow on an IC--, 0009 airfoil. A limited iive-ti.,tion
was also r:ae of the characteristics of C..~.2cf rain tab.
The results of the tests indicated the f:ollo-.ir.T ?Dn-
clusions :

1. ?--.:. slorn of the lift c.:r-e was lare-.t for the
plain sealed flap, whereas ie.I slopes f.r t:.-. 0.50cf
ovcrhanrs were the ra,.Ei as or slightly larger t.han- for
the O.3,'Cf overhab!"... A reduction "n -iope caused by
unreall-;: the gap increased with balan.'e chord.

2. The variation of lift coefficie.t with flap
deflection rallyy increased .wen -. .' a ."r -eiled
and when the nose Pr:..r cher-e fr.':. elliotic-:al to blunt.

3. i r.e fl_ :. lift effectiveness pr.' r-ter a.f
generally decrea-ed v.he-, the over'.-r, c.,h'-rd ci3 s v ii -reased
and ,sa- usually largerr for t'-- bl.ut-r;.nc thra fr the
elliptical-nose overhang. .-alir.- the .cTa increa~cd abf








TNACA AR 'o. L5FO0


for the nol .in flap a n f. L the elliptical-nose ovErrhan,
but .gnerally dccrsac:ed it for the blunt-nose overhang.

4. Sc.lin.- the k.E-p acr the flap nose ,ozdede thec varia-
tion of flap hirnge-mo.nent coefficiLent with anmrl].e of attack
more negative; ch'an.:rig the none shape flror: blunt to
elliptical made this variation more nEtati.ve for the sealed
Cap and iore positive for the un,-'alecd a.

5. The var;i tion oCr iCla'o ir-!,-..oment c '-fficiernt
with flap deflectiorL wav? rgenerr.lly more nrictilve with a
sealed gap than- with an un'i ale d Tap, Changir-ir tbh nose
Ehane frn lA i'.it to ellir tical r;: this variation more
ne.:-tlive it c-: -ll 'i_.tLr inflections and less nr-rcative at
lar:-e fla:p dr-. ect L:..r-.

yhe '- :- n.:e f'a. :-' ninc-' r-rment coefficient with
flap dei l,'l c t n, f.-'r t i n:;!':r ai- ed b .;::t-nose overa'.-i' i,
h2 d a llr, P-Tr '.-aria t Lo i with b;-'.al :ce chord. thar the -*-ange
of flap hl.e-n,-:c1'nt coefficient :",.th angle of attack;
for the cealed tli..t-n;.- overhang, these variati-:.. w.re
ai'ouLt tLhe. cam-rie j n the, ra nio of ':lince chord fr'm .: 0.35cf
to (.,Ocf. .or t-r. F7ral -J .S'. unsealed elli :'ical-nose
ovPrhanr-., th'. cha.i'- of i'lap hinge-moment cr. efficient
with anKle of E.tt.ck i.aid & larger variation than the
change of flan hinc-r-more.nt coefficient with flap -deflection.

'7. cr all j:.n.. i s, unse-.P..- the gap moved the
apro-dynat:t c ." .ntcr f r'.w rt. about 1 percent airfoil chord.
Unsealing the Fap .r i cr-easing the balance chord movc-
th.e center-of-lift position .eIL. to fla"' .-.flection forward
for the blunt-nose and rcar'nard for th;. elliptical-nose
flap.

P. The tab '.'-as -si..-htl:/ more Effr;--tive in chri.'irj.:
the lift and. the fl'p hire no ,:,ent on the plain .f..a than
Ln the "'lap ".:,ith ''..35".- ll ptical-nose over'-ang.


La.n-lc y "e .ial Ar..-..ti cal ITa;:oratory
-'itionr,:1 Ad'.'isor' :Coranittee for Aeronautics
L.aniglcy C ld, Va.








14 iACA ARR No. L5F06

REFEREE CES


1. Riebe, John "., and Church, l0eta: 'ind-Tunnel
Investigation of Contr.l-Surface Characteristics.
XXI medium m ai.d Large Aerodynar.ic Balances of
Two rose Shapes and a Plain Overhang Used with
a 0.40-Airfoil-Chord Flap on an LACA 0009 Airfoil.
.ACA ARR ':. LSCO1, 1945.

2. W'enzinger, Carl J., and Harris, Thomas A.: The
Vertical Vind Tunnel of the National Advisory
Committee for Aerona-itics. iHACA Rep;. T!.. 387,
1931.

3. Sears, Richard I., and Gillis, Clarence L.: 'Wind-
Tunnel Investi ation of Control-Surface Charac-
teristics. VTII A Large Aerod;mramic Balance
of Two :rose Shapes Used with a 3C0-Percent-Chord
Flap on an !;ADA 0015 Airfoil. IACA ARR, July 1942.

4. Swanson, Robert S., and Toll, Thomas A.: Jet-Boundary
Corrections for Reflection-Plane i'odels in Rectan-
gular Wind Tunnels. NACA AiiR Nc. 3E21, 194Z.

5. Swanson, Robert S., and Gillis, Clarence L.: Limi-
tations of Lift'l---Line Theory. for Eti-ration of
Aileron H.i';c-'.'-r!nt Characteristics. TACA CB
S.:. 3L02, 1943.

6. Ames, :1?ton B., Jr., and Sears, Richard I.: Determi-
nation of Control-Surface Characteristics from
IATA Plain-Flap and Tab Data. LIACA Rcp. Njo. 721,
1941.

7. Ames,'MVilton B., Jr.: Wind-Tunnel Investigation of
Control-Surface Characteristics. III A Small
Aerod-namic Balance of Various Hose Shapes Used
with a 30-Percent-Chord Flap on an ITACA 0009 Air-
foil. UA.AC ARR, Aug. 1941.








: ACA u.RR :io. T&FCC 11





TABLE I


ORDIr.TES FOP. iIACA OOCi AITfLCIL

[Stations and ordina-tes in percent airfoil cuicird]


Stt -i n r r e~ rfa i I L:. rurf-Ce
.- -- -- I
0 0 C
1.25 1.1 -1 .42 I
2.o 1..'3 -1.96

1 ..1 --. .7
7. .15 .15
0 1 -. l

.,- ,- -, ... 0


4'? .. .

CO
5'-- ,;' T '- ". T
I ^ '^ -I'- .- (
rr~ l I <, r r



89 l.E iT -]. ..l
90 I.C(' .C9
95 ."0 -. ".'
lo1 ( .1 ) (-.1C)
1O0 ,1, C.


L.E. radiu.-: :'.C9









C v.:.: :: .. ,EiBi'TICS









" .' I


. L


TABLE II


3..R T: ATS FOR 0.35cf AND O.c.50c ELLT TITAL- 'ISE OVERHANGS

[Stations measured from forward end of overhang; stations
and ordinate- rieasured in percent airfoil chord]


0.. 5c, overhang
i


'.5Ocf :verhang


I Station Ordinate q .nti .n O rdinate
I.


. C1
.12
.18
.50
. 1
1. .2
1. 58

S.35
3. .90


.uo
' c7
* u7


.21
.4G2

.43
1.04
'.25
S.4 5

1.76
]. '331.


2. "9O

1.97


03
.15
.J6
.65
i.C5

.15
i 5

3.17




.E67



.48a
1' 00


.21
.42
.62
.8-
1.04
1.25
1.46
1.67
1 .75
1.83
1.92
2.00
2.04

2.04
2.00
1.97


__________________________ .-----.-.--------- ..-~.-.--4---


L.T I" AL ADVISj RY
CO'.1:;I'TTEZ' PF'R :3 ERO::.Il-TICS


--













'IACA AR. "0. .LC.OC


vI




S *. r *O [~- r -
CJ-- r- CO -Z% r-i r- I


r--














*.0


-0





r-1





ri










I.,




..,,






r




'-,









5.'



'-.


*3 0-^ !


3 0 0 0 0 0 ".-' 0 "' o0 r,




I I


j
H | 0 C L .) U 2 02 S* 1: i1 .2 C



. ri r r-r 0 *' e 0 n r D C' 0
1 *-. 'C 0 *2 j.C'0 0 0 0C-


~1


0~ C" tI)


~I

Cl


C-)


Ec-

Sr., c.

r--i r'*L
P-1 a. *
C,^


.1.

,. f l.
c"~ t.'


a) C
0. C,
o n


rt r-

, c:



r--l -H







uJ ,I
C.., *,-


c'0


"J


r
*,- I L ..
.. r,
I-.,


c(
C,
-C'

I"--1

.rl -.

i-, ,--
>- i-l


-.4
ci





,-r



!* F -


a)

IL;


31 4

i-it



















1'-








NACA ARR No. L5F06 18




TABLE IV



PARAMETER VALUES F-R 0.-0c FLAP WITH PLAIN, i.'5cf, AND C,.50C'cf VERHANIC
ON NACA 0009 AIRFPIL



slopes raken at a = 0 and btr = 0~


NATI: AL ADVISORY
CCMMTTrEE POR AERONAUTICS







\





Fig. 1


NACA ARR No. L5F06


C-)
4, 1




! 9



1 1



-it
^^

Y $

\4
I j





NACA ARR No. L5F06


:8 -- 1 c -
/ 25
-/0 30
-/.I I I 1 I I 1 1 I 1

-20 -16 -/2 -6 -4 0 4 8 /Z 16
Angle of o/fac/o, deg
6/ure 2 .-AeroodS/ynomc section character/6st/c af
an /VACA 0009 aorfo// w/,fI a 0.20c p/o/n f/lp.
Flap gap, 0005c; tab, 020cCf, lab gap, 0.00/c;
6 =0 NATIONAL ADVISORY
COMMITTEE FOR AIElIDIAUTICS


,N
)AI
*k

NN


/


Fig. 2






NACA ARR No. L5F06


-
-4


.08

.04

0


-.04-

-.08



1q1



. -J-.zo
Q





4 -.3
-3




-.36


-.40


-4 41 i i 1 1 I I I i I I I I i I I
-20 -/6 -/Z -8 -4 0 4 8 /2 16
Angle of altack, .,, deg


Figure 2 .- Concluded.


NATIONAL ADVISORY'
COMMITTEE FO AEAIOIAUTICS


Fig. 2 Cone.





NACA ARR No. L5F06


14- ------- -





i .8 f '
S-(--- ---- --- ---deq) -- --
"".6 -- -


-.

2 .i
^ *2 ---^-- f

c -2

E" /
-0 ---^-------V-----o0/0-











an /ACA 0 0 0 9 irfo// ztlh a 0. c pl/in
-----------------6----


-l9 -e of' at co--








f/op. Flap gap seale d; tab ,02 0 cf; lab gap, 000/c;
"" =, 7) = =----







St L *NATIONAL ADVISORY
COMMITTEE FO AElONAUTICS


Fig. 3






NACA ARR No. L5F06


Fig. 3 Cone.


5
~I .



0


SI.I04





-./6o i- 10 -oo
(dei
-.20 oO

-.24-- --0----- -- "

-.28 -Z -8 -- --



36 -










Anyge o alltack, ao, de NATIONAL ADVISORY
:ure .-Co cuded. COMMITTEE FN AEIAHAUTICS






NACA ARR No. L5F06


-.-------------$ i- -A

.8 --------__-----



.-4 5-











0 -
/ ,/0


-4 ,-,- -- -


6





/._

-2_0 -/6 -/2 -8 -4 0 4 8 /Z /6
Ang/e of a ack, Co z deg

Figure 4. Aerodynam'ic secl-on chorocteri/scs
of on /V'ACA 0009 io/ur/bl /;, vA 0. 20c f/op
hal/'-y a 0.3J-cf oerhany /,y*h blunt nose.Flap
gaqo, O.OOSc fab, 0.20cf; /qb gcp, O. 00/c; 6 = 0


NATIONAL ADVISORY
CONNITTEE FM AEMLIUTICS


Fig. 4






NACA ARR No. L5F06


0



-.2


.08

.04

0


-.08 \ 5-











-.08 -
a .28 -- '- -- -
L-/ --J-L-- -- 5-- ^----




32--

-.36 -
-20 -16 -/Z -8 -P 0 8 1 /6
Angl/e of allttach ao deg

Figure 4.- Con c ded.


NATIONAL ADVISORY
COMMITTEE F0 AEUIIUTICS


Fig. 4 Cone.


4z



o
to $
8 a

o
1
ll






NACA ARR No. L5F06


N



A)
lb

Z
i



B


.0

.8

.6

4

.2

0

-:2

-4

-6

.-8

-10


-/.2


-20 -/6 -/Z -8 -4 0 4 8 /Z /6
Ang/e of ofttack ccW deg
Figure 5.- Aerodoyncvmi/c section characterl/sfcs of
an /A CA 0009 or/b7// w/1M a 0. 20c f/aPo h/o-g
a 0. 35c, overhancy' Iv/th /ln7/ nose f/gop gap,
sec/e d; tab, 0.2Oc, ; tab gap, 0.00 c ; 6t = 00
NATIONAL ADVISORY
CONNITTEE FOI AEtONAUTICS


Fig. 5




NACA ARR No. L5F06


F




zl
Pi






I.o


-20 -/6 -/2 -8 -4 4 8 12/ /6
Ang/e of cttackh,cA, decg


F-iure 5 .- Concluded.


NATIONAL ADVISORY
CONNITTEE ro0 AERONAUTICS


Fig. 5 Cone.







NACA ARR No. L5F06


10 -_ _4 _

/2----------------
/0

K /"
----- -- --

















L 5
/0---------------- 5 -/0
/.0 -- ------ ---















lO "/
'. ,6 ('deq- ,- _

























Ang/e of at,,rch, c, deg

1jure 6.-4eroo'ywmk second charactendice of
-f c" 47 .c. d e e


















an- ACA 0009 airfo// vh 0.20c //ap halwpy
a 0.3Jc,, overhang wi/h e/ipfa'/ nose. ap
qap, o. OOJc; /ab, 20cf; lab gap, 0.00/c; 6 =0
--^ 4^ --- -- 0.0c ovra q /hel/tc oe.F
ap -.-O0 c -b- .20c l -b -, 0001 5, O


NATIONAL ADVISORY
COMMITTEE FOI AEtDNUTICS


Fig. 6






NACA ARR No. L6F06


,
IZI










A




1
q3^




qj


"2.


.04

0

-04

.08


-/6

-20

.24


-40


-20 -/6 -12 -8 -4 0 4 8 12
A4ng/e of a//fac a dey
,gure 6 Copc,c'eudod.


NATIONAL ADVISORY
COMMITTEE FR AERONAUTICS


Fig. 6 Core.






NACA ARR No. L5F06


-6

-/0

-1.2


-20 -/6 -12 -8 -4 0 4 8 12 /6
Ang/e of oT/ac, o, dei

Fuare 7. -Aerodynamic/ section characfer/a/ics
of an /VACA 0009 oirfol w#th a 0.20Oc /oap
hayg n a 0.3JJc overhang ,Y'/t e/fiptfco/ nose. lap
gap sealed; fab, 020cf lab gap 0.001c c6, = 0


NATIONAL ADVISORY
COMMITTEE Fr IAERAUTICS


Fig. 7





NACA ARR No. L5F06


I






.4


.04

0


-04


9 -/6
008

SO16


e- 0


,u <


-32

-36


-20 -/6 -/Z -8 -4 0 4 8 IZ /6
Angle of act'ack, zo dey

,tl're 7. Concluded.


NATIONAL ADVISORY
CONNITTIEE FO1 AEOIIAUTICS


Fig. 7 Cone.


I


?






NACA ARR No. L5F06


NATIONAL ADVISORY
CONNITTEE FM AEMMAOUTICS


IF =,'=/ L/ I I=I I



--- .(oe )
-- __--- -







010
S-6- --/ -/
.6----------5-^--(de---





/. 4-- -- -0- /-
5-..
Io 0 /!,

-" ,. -,, u/I~~ I ~ o-


. -- -!-/----- o -
-6 -- //o--








Angle of a/tacA, x d e
?/. <>a^- -- -,----


-/.z --2- -




Fl/are 8.-Aerodynam/'c section characteristic of
an /ZVACA 0009 oirfo//, n//'h a 0.20c flap
hav/ny a 0.50c, overhang with h/ant nose;
Flap gap, 0.005c tab, 0.20c, ; tab gap, 000/c;
6=o0.


Fig. 8






IJACA ARR No. L5F06


r u



(S
-h
1Q.


Nl


0

7/

-2




.08

.04

0

-.04


.4



-28
.-/O


i .^ -24


-20 -/6 -/I -8 -4 0 4 8 /2 /6
,4n/e of affoc7 ao ;,,deS

F/gQre 8 .- Con/uded.
NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS


Fig. 8 Cone.


p,






NACA ARR No. L5F06


-8

-1.0


-20 -16 -/2 -6 -4 0 4 8 /2
Angle of oafeck, co deg
Figure 9 .-Aerod~,noamrc sect/ic, chorocter/s,/cs of
an /,4VAC 0009 airfo// w/V, o. Z Oc 7/op
haoy/'7 0. 50c, overhon7g Wl'h /unft nose.F/ap
gap sealed; aob,0.2Ocf; /ab gap, 0001/c; 6t =0.


NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS


Fig. 9





NACA ARR No. L5F06


0 P
-s




C3






SU


q )


.08

O4.

0

-04

-08

.12

-/6


-20 -/6 -/2 -8 -4 0 4 8 12 /6
Anlqe of fftoc, c o, o de

r~uare 3..- Concluded.


NATIONAL ADVISORY
COMMITTEE FOI ArtROiUTICS


Fig. 9 Cone.







NACA ARR No. L5F06


O
V%





u
v0
U)


0
'I-


-20 -/6 -/ -a -4 0 4 6 /I /6
Angle of attack, cc., de9

F/oure /0. ,erodynacm/ic section ,charoc+cer/'it/c
of a.n /VACA 0 009 aorf'o/ i1y-h a 0. O20c f/ap
ha/n7 o' O0. J5Oc overhan/ l wi/h e/;h of/co/
nose. Flap gap, 0.005c; tab, .020c, ; lab gap,
O.000 c 6; = 0.


NATIONAL ADVISORY
CONNITTEE FY AEIOIAUTICS


Fig. 10






NACA ARR No. L5F06


N
I








o *
P)
'1


-20 -/6 / -8 -4


0 4 8


Ang/e of attach, oco deg


F/qure /0. Concluded.


NATIONAL ADVISORY
CONNITTEE FD AEIRIAUTICS


Fig. 10 Cone.






NACA ARR No. L5F06


5-


i-


'II

//
1 '
I. -----------_ I
---------------/--------Z ~II








49 /
.4 /-- 7 --7
-^-.4+!-!- -

l' i ^i =i =
-8 ,2 I / 2.0== ===


-20 -/6 -IZ -8 -4 0 4 8 /Z /6
AnQ/e of attack, Co., deg
Agure I/. Aerod/'yam/c secf/on characfer/stc/c
of a7n /YA CA 0009 a/rfo// wl/ a O. 20c f/ap
har/,iq a O.00c, overhlc7ny W/fih el/pf/ ca/
nose. Flap gap sealed; lab, O.2Ocf, lab gap,
S00/c; 6, =. 0. NATIONAL ADVISORY
CONNITTEE FUI AiIIAUTICS


Fig. 11






NACA ARR No. L5F06


I
-- ---
_q) _


^$ /~ ^ -^ 1 1/ 15Id-7
t
-./ ^-_. _- -_ _

-. --- dq-- C


.R)z

-2
0 5
.^08---- -- --- -- -



^ o _ _rde-- -- --







:24


-20 -16 -/2 -8 -1 0 1 8 /Z /6
An /e of a/ac/r d da

F/'ure //.- Conc/lded.


NATIONAL ADVISORY
CONNITTEL FrO AIrONAUTICS


Fig. 11 Cone.






NACA ARR No. L5F06


/0N I ITIL FCUR AERUtU IIL


.100 -- --










.040


.030 -







b -.40 -


50 __

0 .J .2 .3 .4 .5

ch ,/cf

Figure /2 .- Varial/on of airfoil sec ion
/0/ -parame/ers wilh cverhonq on
/VACA 0009 a/rfo/l. olap, o.20c; f/lp 9ap ,sealed
and 0.005c. Tod, OZOc; tA ob p, O00/c1 6t =00.


Fig. 12





NACA ARR No. L5F06 Fig.









Io I!




q 6
Ll I



\ \ \N






--
11 7








\ o o



I I I^I
o -o
VO P11V V: 9 Q
O^ ^. r o





^^^^-Il
--- --- -
/
JV puC D^ ^


13






NACA ARR No. L5F06


qj


I












-1


'a


0 4 8 12 /6 20 24 28 32
F/ap def/ection,i, ,de


Fagre /4.- Increnent of o/rfo// sect/bn prof/ e-droy
coeff/o/ent caused by deflection of a 0.20c
p/q/n f/oip with gap sealed and with 0.006'-
gap. Tab, O.ZO c, gap, 001/c; 6 =0.


NATIONAL ADVISORY
COMMITTEE F0 AEIRUUITICS


Fig. 14






NACA ARR No. L5F06


.0 -----------
S.06 -----------
^ .06 -------------L-^-------/
^ -- --(-k9) ^-^ --
S- Sealed q
1 .04 a5.0c overhang '_ -----0.005c



O0 0

f' .0-------------^-(dq)--- c
S.0E2/, .(e





rz,
So0
06 (de)-------

.04 -- 0.35cf overhanga----

.02



-02_ I.....
0 4. 8 /2 /6 20 2,4 28
Fhp def/ecfion deg
Flgure /5.- Increment of o/rfo// l ect/6in prof/le-dray
coeff/icent caused by def/ecf/on of 0.2Oc f/apo
hav/g79 0. 3c and .L500,f /Iunt-no-e overha7ngs
w/th / o sea/ed and w/t/f 0.00-ec gap.
Tab, O.ZOc f ga p 00/c; = 0 a
NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS


Fig. 15






NACA ARR No. L5F06


-20 -/6 -/2 -8 -4 0 4 8 /2 /6
Angle of attack, oc., deg
F/lure /6 Aerodynam/ic Jectio/n c0/racter/Jh'
of an 4,4A CA 0009 a/.rfo/l w//1 a 0. 20 c pain
flap hcv/ng 7 0.20cf plain tab with S= i.
F/lp gap sealed; fab gap, 0.001/. N.ATIONAL. ADIOY
COMMITTEE FOl AMIOAUTICS


Fig. 16







NACA ARR No. L5F06


QI,


.08

0

-08

-/16


-24

v -32









u
II^-J6


-72

-80

-88


-.96 i I 1 1 11 1 1J .1.I L 1 1 1IL
-20 -16 -/2 -8 -4 0 4 8 /2 /6
Angle of attack, aoc, deg
F/'gLre /6 .- Cont/nued.
NATIONAL ADVISORY
COMMITTEE i1 AEM1AUTICS


Fig. 16 Cont.







NACA ARR No. L5F06


.OS
,Ob





-.04
0
IQ

703^


--


O





.0
I


-/6

-20

-24

-28

-32

-36

-.40


-20 -/6 -/2 -8 -4 0 4 8 /2 /6


Angle of attack, oc., deg
Figure /6. Con c lu de d.


NATIONAL ADVISORY
COMMITTEE FOR AEIIAMITICS


Fig. 16 Cone.






NACA ARR No. L5F06


-6
*i 6

.4

N .
.0


1


'^-6

-8

-1.0


- 20 -/6 -12 -8 -4 0 4 8
Ang/e of attack ,,o ~ de


NATION. ADVISORY
CONNITTE FIl MlOMUITICS


(de, -,/
El / 0


v 0





I





,' / = o



/ --/i I 20---- eg -

,,_ Z.,.! .. /o
S20 -
! I -zo -


/2 /6


F/i are /7 .- 4erod,'namic secT/b/o choracter/st/cs
of an /4/ACA 0009 airfol with a 0.20c f/ap
hav/n1 ac7 0.3Jc overhQng wi/th el//f/cal
nose and 0.20cf plain tab with = /
Flap gap sea/ed; iab gap,0.00/c. f


Fig. 17


-I/






NACA ARR No. L5F06


S.i --------------
^ -2 o 20_ _..-,,-- .... ,







6 -_ ,-


S- .16,- ,,- -f--- .1o rde-
t *08 -.-- .--- o




S-d6f6




32 ---------------- -----------

-740__- -



20 -16 -/ -4 0 4 8 /2 /6
An /e o7f offttac, a de
Fi-ure /7 .- Cont inue d.
F/'gure /7 .- Continued.


NATIONAL ADVISORY
COMMITTEE FNM AIMoITIS


Fig. 17 ConL.







NACA ARR No. L5F06


i40
I- .o0







S08






. :20



S-24


-32


_-__-I I/I-
-+---t


0- _






r
-- -- -- / _







,1 I


-__-_--_ ---H
--- eg/




-----_----------- 2-
---1"-- gC-
_~~ ~ _ _i -
~I I I I I I I I I I


-20 -/6 -12 -6 -4 0 4 8
Anq/e of af'toc/< ,co, deg


/12 /


Figure /7 .-Conc/Lded.


NATIONAL ADVISORf
CONNITTEE FI AEMIAUTICS


Fig. 17 Cone.







NACA ARR No. L5F06


NATIONAL ADVISORY
CONNITTEE FW AEm 01MTICS


-- --7 -




-- --------- ol





t i



20
--_ -^ _--_ --
----~ /-/- / ?
_4 ^ /_ < ( y
^ __, _
_/ IL (? _
_//_ .d _
-^i_ oOJ0 _


-0O -16 -1/ -8 -4 0 8
Angle of altack, cro, deg


Figure /8. Aerodynam/ic section choracfer/sf/cs
of VA CA 0009 o/rfo/l with O.20c p/a/n f/op
having 0.20cr pa/on tab. Flap gap, sea/ed fab
qap, 0.00/c 6 -= 0.


N
Ks
:

5j




N


(~j
Is.
e


-/.0

-Ip


/2 /6


Fig. 18


. (u







NACA ARR No. L5F06


I





4O
.91


Ik
^$

^


-. *%

rpl


0

-.1




.08

.04-


-.08

-/2

-16

-20


-28


.32 1 I I l I7II I l l l l l l l l I I I
-20 -16 -12 -8 -4 0 4 8 /2 /6
Angle of fftack, a:o, deq


Figure /8.- Con inued.


NATIONAL ADVISORY
CONNITTEE FI AEOMMITICS


Fig. 18 Cont.







NACA ARR No. L5F06


o-,

t


I








GD


.08

.04

0

-.04

:.08




-/6

-20

24-


-20 -/6 -/2 -8 -4 0 4 8
Ang/e of attack, ro, deg

Figure /8.-Concluded.


/2 /6


NATIONAL ADVISORY
COmNITTEU Mmt IuCS


Fig. 18 Cone.






NACA ARR No. L5F06


OI





7 20

7w




Urdeg)
/' ------------









.2 0

150

.2 20
(30
/t - -













-20 -/6 -/2 -8 0 4 6 /2 /6
Angle of attacK, am, deg
Fi ure 1 9.-W lr/rbn of reul/fant pressure coefficient amss
fhe 0.20c plain-flop nose seal wt-h angle of
atffachr on n N,4ACA 0009 /ronil. Tab, 0.ZO c,;
gap, O O0/c; t =- 0


NATIONAL ADVISORY
CONNITTEE FO AInMAUTICS


Fig. 19





NACA ARR No. L5F06 Fig. 20






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