Wind-tunnel investigation of control-surface characteristics

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Title:
Wind-tunnel investigation of control-surface characteristics
Series Title:
NACA WR
Alternate Title:
NACA wartime reports
Physical Description:
17 p., 33 leaves : ill. ; 28 cm.
Language:
English
Creator:
Riebe, John M
Church, Oleta
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 )
Aerofoils   ( lcsh )
Aerodynamics -- Research   ( lcsh )
Genre:
federal government publication   ( marcgt )
bibliography   ( marcgt )
technical report   ( marcgt )
non-fiction   ( marcgt )

Notes

Summary:
Summary: Wind-tunnel tests have been made to investigate the characteristics of an NACA 0009 airfoil with a 40-percent-chord flap having medium and large aerodynamic balances of elliptical and blunt nose shapes and having a plain overhang. The results are presented as aerodynamic section characteristics for several flap deflections with the gap at the flap nose sealed and unsealed. Tests were also made to determine the effectiveness of a tab, which was 20 percent of the flap chord, on the plain sealed flap and on the 35-percent-flap-chord elliptical-overhang flap with gap sealed. The pressure difference across the flap-nose seal was also determined for the plain sealed flap.
Bibliography:
Includes bibliographic references (p. 13).
Statement of Responsibility:
by John M. Riebe and Oleta Church.
General Note:
"Originally issued March 1945 as Advance Restricted Report L5C01."
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 - 003807479
oclc - 126858452
System ID:
AA00009380:00001


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Full Text


VA(/L-/7
ARR No. L5C01




NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS





WARTIME REPORT
ORIGINALLY ISSUED
March 1945 as
Advance Restricted Report L5C01

WIND-TUNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS
XXI MEDIUM AND LARGE AERODYNAMIC BALANCES OF TWO
NOSE SHAPES AND A PLAIN OVERHANG USED WITH
A O.O4-AIR)FIL-CHORD FLAP ON AN
NACA 0009 AIRFOIL
By John M. Riebe and Oleta Church

Langley Memorial Aeronautical Laboratory
Langley Field, Va.







1,j-> 7 US,_.k
i{ i .""', IFLO,,
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 175




































Digitized by the Internet Archive
in 2011 with funding from
University of Florida, George A. Smathers Libraries with support from LYRASIS and the Sloan Foundation


http://www.archive.org/details/windtunnelst00i





|-^ -





IJACa AF.- Io. L5001 RESTRICTED

N'ITTC:!AL ADVISORY CO;.7ITTEE FOR AERONAUTICS


ADVA"'CE RESTRICTED REPORT


..Tl-ri:.'EL I:I'', IGATION OF CONTROL-SURFACE "CHARAC EISTICS

-I IETrI:' AND LARGE AEROD-I".-IC F.'- T~.C'3 OF l"0

'SE S ..ES 'D A PLAIN OVERHANG USED .

-0..40-AIRFOIL-CHORD FLAP ON AN

fACA 0009 ATJ'IL

T John 1. Riebe and Oleta Church





-..,~n-1i..il tests have be.n made to investigate, the
cl-r,-i.;ter.istics of an NACA 0009 airfoil with a 40-.ercent-
c- or1 fi-. Pa- igi medium and large aerodynamic balances
oif ili.ptlc.l .1d bl-unt nose shapes and having a plain
Cvr..n. i e-sults are presented as aorodynamlic
sect.rion *.rcr.:tristics for several flap deflections
t ti "-. r t the flap nose sealed and unsealed.
T'sts v'.'.e 1 s made to determine .the effectiveness of
a ta'.', 'r-ilh w s 20 percent of the flap chord, on the
'.la-in seai-d fl.ip and on the 55-: rcent-flap -chord
elliut ic, l-oC1-5arg -flap with ..> sealed. .-, pressure
c iff:~eSr.2: dcr3oss the flap-nose seal was also determined
for :i.e plan s- aled flap.

The results indicate that the slope of the lift-
coeff'icie.it curvo was approximately the same for all
seale.d-gEo c,.nitions, except for the fla- with a
5.0-;oecent-flao- hord elliptical overhang for which the
sloCe vas -aibLojt percent larger than the average. A
4--e r:-:nt r;oi.m -con of slope occurred as a result of
u.:seillin tL.e .:o at the flap nose on the plain flap;
whe:rea- a 15- t.-- 17-percent reduction occurred as a
re-.uilt cf ltu-eaiing the gap at the flap nose on the
flap ,.ith aerodryn,Iic balance. -. change in lift with
flap delleticn was found to increase as a result of
sealing the egp at the flap nose .and of changing the
nose sha,-e frc.n elliptical to blunt.


RESTRICTED










NACA A N HoI. L5G01


The effect of unsealing the gap (except for the plain
flap), increasing the balance length, and chnrg-ing the
nose shape for, elliptical to blunt was to make the rate
of change of flap hin-, moment with flap deflection (at
small flap deflections) and with angle of attack more
positive. Some overbalance was found on the 50-percent-
flap-chord overhangs.

.-:en the lift was varied by changing thi angle of
attack at zero flap deflection, the center of lift was
at the 24-percent-chord station for all overhangs tested
with gap sealed. The center of lift t;e to angle of
attack and that due to flap deflection generally moved
rearaward as the gap wac unsealed.


7:7 ".3DTCTI 0:


The ...Ci. is conducting an extensive investigation to
provide experiqmental data for design purposes and to
deter:.':re the section characteristics of various types
of flap arrangement suitable for use as control surfaces.
The investigation is beirn made in the Ia.-ley 4- by
S-foot vertical tunnel and has included tests in which
flap profile, traillng-edge :iE.ge, gap size, flap nose
shape, ard balance-chord length have been varied. Most
of these tests have been made, however, of a 70-p'rrcent-
chord flap. In the present report, the investigation is
extended to determine the effects of flap nose ,., pe and
balance-chord length on an airfoil having a 40-percent-
chord flap. Data on the pressure across the seal of the
plain-flap nose and a method& of applying these pressure
data in the design of internal balancer are presented.
Tab data are presented for a flap with a plain overhang
and with aerodynamic balance.


ST .BOLS


The coefficients and the symbols used are defined
as follows:

C, airfoil section lift coefficient (-
qc/ do
cdo airfoil section profile-drag coefficient -

Acdo increment of section profile-drag coefficient due
0 to flap deflection











NACA ARR Fo. L5C01


cm airfoil section pi tching-moment coefficient (--

ChI fla- section :hine-moment coefficient ---
qcf

Cht tab section hinge-moment coefficient [ 2-1 )
\ ot /

S/PT, PTA
PR resultant Dressure-coefficient "-Pq

vwe re

I airfoil section lift

do airfoil section profile drag

m airfoil sectiicn .ritching mrnoment about quarter-
chord no'rnt of airfoil (positive moment moves
nose of airfoil up)

hf flan section binge moment- about flap hinge-axis
(positive -monent moves .railing edge down)

ht tab section hinge moment about tab hinge axis
(positive moment moves trailing edge down)

c chord of basic airfoil with flap and tab neutral

Cf flap chord from flan hinge axis to trailing edge

Ct tab chcrd from tab hinge axis to trailing edge

q free-slr's-cjn dynamic ress i.cre

_PL static pressure on lower surface of seal

PU static pressure on uoper surface of seal.

eb balance chord

ao angle of attack for- airfoil-of infinite aspect
ratio positive e when nose of airfoil moves-up)-

6f flap deflectio-n .ith respect to airfoil (positive-
when tr ai lin_ edge is deflected downward)

5t tab deflecticn -:ith respect to flap (positive
when trailing edge is deflected downward)










'NA]A ARR No. L5C01


also


ftoo






cf c
r/a,,bt

Chf=
a ,5
6 f CEf 6t




Chfsf =\Ltf 6fo,,t




Lc = \%-605 6t

= (.6Cm>
cI / La,,5t ( )c7 i, 6t


Tie subscripts outside the parentheses represent the
factors held constant during the measurement of the
parameters.

APPARATUS ATD MODEL

-. tests were conducted in the Langley L- b-- 6-foot
vertical tunnel described in reference 1 and nc3iified as
described in reference 2.
The model, when mounted in the tunnel, spanred the
test section except for clearances of 1/52 inch between
the model and the tunnel walls, "'Lth this tyne of
installation, two-dimensional flow is closely anproxi-
mated and the section characters cs of the airfoil,
t'ie flaa, and t-e tab mayr be detesr ined. The r.d.l
was attached to the balance frame by torque tubes that
extended through the sides of the tunnel. T.e angle of











!',-.A ARR No. L5001


attack was set from outside the tunnel by rotating the
torque tubes with an electric drive. Flap deflections
w\ re set by means of an electrical position indicator
N:i tab deflections were set with a temiplet. The hin3e
'ean-s of the flap were.measured with a special torque-
oiJ balance built into the model. For the tab tests,
t-_.b hinge moments were taken by an electrical strain
.a.e installed in the model. For the plain sealed flap,
tLe pressure difference across the seal of the gap at
th::e flap nose was measured on a mano:meter.

The 2-foot-chord b7 4-foot-span model (fig. 1) was
constructed of laminated mahogany (except for a steel
tub), was aerodynamically smooth, and. was made to con-
form to the ITACA 0009 profile (table I). It was
aqi.:ipped with, a 0.40c flash and a 0.20cf plain tab.

The fla-o had a rlain-nose overhang with a radius of
a-,oroximately one-half of the airfoil thickness at the
flap hinge axis and was so constructed that it could be
fitted with aerodynamic balances that were 55 and 50 per-
rit of the flap chord. These balances were of blunt
a"-!, elliptical nose shape. The elliptical nose was a
ti.-e ellipse faired tangent to the airfoil contour at
th-e flap hinge axis. The ordinates for the elliotical-
S:se overhang are given in table II. The nose radii
:,cv'iwn in figure 1 determined the blunt and plain nose
s!.pes. The various overhangs consisted of nose blocks
'i.t could be attached interchangeably to the flap at
h-: hinge axis. In order to keep the 0.005c gap at the
flap nose (flap gap) constant, these nose blocks were
,Tiarched by interchangeable blocks in ite airfoil just
forward of the flap. An airtight fabric connected the
fl:p nose and the forward part of the airfoil for the
se:led-gap tests.

'eT 0.20cf tab was made of steel and the nose
radius was approximately one-half of the airfoil thickness
a,: 1the tab *L.- axis. The gap at the tab nose (tab gap)
w-vs 0.O01c.




In order that the test results raay be found easily,
t`- various flan configurations tested and the figure
nu'x-bers of the corresponding plotted data are given in
table III.











i'A ARR Po. L5COl


t. tests we'e made at a dyna-mic prs-ssure of
15 pounds per square foot, which corresponds to a velocity
of about 71 iiles rer hour at standard sea-level condi-
tions. ?he test ReyTnolds number was about 1,350,000.
Since the tunnel turbulence factor is 1.93, the effective
Reynoids number was a-oroximately 2,570,000. The Mach
number for these tests was about 0.09.

Se max.rum error in angle of attack annears to
be-. 0.2. It is estimated that the flare and tab deflec-
tions were set to within 0.2.

An experimentally determined tunnel correction was
anplied to the lift. I'.e angle o0- attack and hinge
ionients were corrected for the effect of streamline
curvature induced hy the tunnel walls. The method used
to determine these corrections is similar to the
theoretically" dcerfived analysis presented in reference 3
"or finite-span nloels. T-. increments of dr:- are
tho.g it to e reasonably inder-ndent of tunnel effect,
although the absolute values are subject to an undetermined
correction. Inaacc~rac in the a.'odel construction and
in the assesmbl- of Ih-e interchanrieable blocks probably
caused '.he small amount of flap hinge moment at zero
anale of attack and flap deflection.


DISCUSS n''

Lift


iTe lift-coefficient curves for the flap with a
nlain overhang and with aerodmnamic balance are shown in
figures 2 to 11. 'ith the :ap either sealed or unsealed,
the lift-coeffioient curves were nonlinear at large
flap deflections.

The slope o' the lift-coefficient curve cl
(table ) was arproximately the saiie with gap sealed
for all flap arrange-ments --a'dless of aerodynaric-
balance shape or length except for the 0.50cf elliptical-
nose over rn:" for which the slr;,e was about 3 -. rcent
larger than the average. TUnse.ilr,- the -ao caused a
I.-oercent reduction in slone for the flan with a plain
overhang and a 13- to 17-nercent reduction for the flap
;with blUnat and elliptical overhangs. For a given balance











NACA ARR io. L5C01


chord ani' with gap sealed, c was arproximately'the
same regardless of nose shapes.

The change in lift with flap deflection cf

increased when the flap gap was sealed and when the nose
shape was changed from elliptical bo blunt. The flap
lift effectiveness cgf varied in a similar manner
except that, in the case of the 0.50cf blunt-nose over-
hang, af decreased when the gap was sealed. It should
be remembered that the parameters shown in table IV
were measured over a small flap-deflection ri.rre (00 to 50)
and therefore are used mainly to compare the various
flap configurations tested.


Hinge 'oment

The curves of flan hinge-moment coefficient as a
function of angle of attack at a constant flap deflection
for the flap with -nlain and balanced overhangs are also
presented in figures 2 to 11.

For the 0.50cf blunt overhang with gap both sealed
and unsealed and the 0.50cf elliptical overhang with
gan unsealed, the aerodynamic characteristics at large
flap deflections were not determined because of violent
oscillations that might have damaged the tunnel apparatus.
Ranges in which oscillations occurred are noted by dashed
lines in the hinge-moment curves. Similar oscillations
encountered on another flap fitted with an aerod-.n- ilc
balance are discussed in reference 4.

The hinge-moment parameters presented in table IV
indicate that an overbalance condition occurred for the
0.50cf blunt-nose overhang with gap either sealed or
unsealed. The 0.50cf elliptical overhang had a positive
chfa for both gap conditions and had small negative
values of chff for small flap deflections to about 50
(figs. 10 and 11).

rWen section data are applied to finite spans, the
aspect-ratio corrections for streamline curvature are
always positive (reference 5). Since the hinge-moment











NACA ARR "o. L5C01


parameters "or several a".an-ements of the flap with
balanced overhangs are very small a-v the signs critical,
the slopes may nass through zero and an overbalanced flap
may result.

-"e effect of seeing the flap 'ap was to make chff
fa
and chf.f more negative except that, with the flap

having a plain overhang, the o-:osite effect occurred.
Increasing the balance length made both Chf. and Chf

more positive. For a given balance chord, greater balance
was obtained at small flap deflections with the blunt nose
than with the elliptical.nose,. Examination of the curves
shows, however, that, at large fla-r deflections for the
0.35cf overh:n the elliptical-nose overhang had the
greater balancing effect. The variation of the hinge-
moment parameters with overhang for the elliptical and
blunt nose is shown in figure 12.

Because the ''ne-'morent naraneters shown in table IV
and -jure 12 represent the slopes of the curves at zero
flap deflection and an;le of attack, these parameters.should
be used mainly as an indication of .the relative merits of the
different flan nose shares. Because the tabulated slopes
are valid for only small ran-es, the slopes from the
hinse-noyent-coefficient curves rather than the values
of table IV should be used in calculating the- charac-
teristics of a control surface.

Th: present investigation did not include tests to
deter-ine the effect on flan hinge moment ofFsealing
the tab gap. It is thought that the flap hinge moments
for a flap without a tab (or with tab gap sealed) might
vary somewhat from the flap iinge moments of the model
configurations tested with tab gap unsealed.


Pitching momentt

The values of the pitching-moment parameters (mc"1ft

and (Cmc)ao, t in table IV determine the position of

the center of lift with respect to the quarter-chord point
of the airfoil. When lift was varied b' changing the
angle of attack with a ,la deflection of 0, the center











TACA ARR ::o. L5C01


of lift was at arnroximately the 0.2.:c station for all
overhangs tested with gan sealed. "- sealing the o'an
had-~o effect on t-he center of li.ft. of the n.ain flan
but moved thLe center of lift rearward to the 0.25c sta-
tion for the 0.75c overhang and rearward to the c,26c sta-
tion .or the 0.50c overhang.

The following table gives the position of the center
of lift caused by flap deflection:

Position of center of lift caused
by flap deflection

Pa- Plan aO. 35cf overhang, 0.50cf overhban
Plain .
overhang i B~lnt Illlipticali Blunt Elliptical
nose nose nose nose

Sealed. 0.57c 0.5Sc 0.57C 0.59c O.58c
0.0050 .3 .350 .4c


T'.se data indicate that the center of lift generally
moved rearward as the flap ap was unsealed. Increasing
the balance chord and changing the nose share from
elliptical to blunt moved the center of lift rearward
for the sealed-gap condition and forward for the unsealed-
gap condition.

The position of the center of lift caused by flap
deflection is a function of the aspect ratio (references 5
and 6) and-moves toward the trailing edge as the aspect
ratio decreases.


Drag

cause.of an undetermis ne ~ tunel correction, the
measured values of drag cannot be considered accurate;
relative drag val~ es are thought to be -reasn.:Iabl
independent of tbunel effect and ,were therefore used.
T'e smallest percentage increase in- rofile-drag coef-
ficient caused at zero angle of attack, -.and flap deflec-
tion by replacing the plain flap with a flap with
balanced overhang was obtained with the blunt-nose
overhangs. e increase in .c ranged, from 0.0006











10 1..A ARR No. L5C01


for the 0.35cf overhang with fla sp sealed to 0.0017
for the 0.50cf overhang with flap g:ap. sealed. The 0.50cf
elliptical overhang with flap gan sealed had the largest
increase (0.0037) in cdo over that for the airfoil with
the plain flap.

T1i, increments of nrcfile-drag coefficient caused by
fla drflection Acj for the flap with a nlain overhang
(fig, 1l) were .----erallv larger w'th the ap onen than
.'t' t-e gap sealed. Since the blunt-nose overhang gave
s-ialle: increments of drag than the ellintical-nose over-
bang at shiall flao deflc-tionls srch as may be-necessary
for the tr.m change the increments of drag are presented
for onl-- the 0.35cf and 0.50cf blunt-nose overhangs
(figs. 1i and 15, resnectlvely). For the 0.55cf blunt-
nose overhag, lower increments of drag occurred with
gap unsealed than with gap sealed. The 0.50cf blunt-
nose overhang bad lower increments of drag with gap
sealed except that, at an angle of attack of 80, the
increments were larger with gap sealed than with gap
unsealed.


Tab Characteristics

Only a limited investigation of tab characteristics
has been iade because the tab characteristics of a flap
with aerodynamic balance are generally independent of
flap nose shape (reference 7) and are similar to those
for a tab on a nlain flap (references 2 and 7). The
present investigation included tests of balancing and
unbalancing tabs on the olain sealed flap (fig. 16) and
on the sealed flap with the O.05cf elliptical overhang
68t
(fi-. 17) with = -1.and.l. For the tests with bal-

ancing tabs, 6t = -1 was found to be too large- since
some overbalance occurred.

a-c flap with the 0.50cf blunt-nose overhang, which
was found to be overbalanced throughout most of the
deflected range, could be -~o.ified by usin' a tab
deflected in the same direction as the flap. This
arr -i- -.lt should increase the lift effectiveness and
provide the desired hirn.e moments. No data have been
obtained for this condition, however.


I










I'AC. A53R No. L5C01 11


Pressure Difference across the Plain Flap Seal

"1-e variation of resultant pressure coeficient
across. Thhe seal of the nlain-flap nose with an.le of
sttac!: at a constant flan deflection is shown in figure 18.
'"'e c1..r-e in resultant pressure coefficient with ani;1le of

ata:l: t aa: was generally found to increase with

incr-eas ;.ang fla- deflection.

The resultant pressure coefficient of the plain flap
is u=f-i. in determining hinge-moiont coefficients of
flars ..'Ith internal balances. It can be show-n that


Chi = Cho + p (1)

w v: rn

cs section 1: : o-moment coefficient for flan with
'fI.. internal balance

section hinge-no-nent coefficient for rlain
flap with gar sealed

P-. resultant pressure coefficient
( *.2 t/c,2
S= (see fig. 19)
2
t semithickness at hinge

data of figure 1 can -e. used with that of fig-
vr:? co determine the flap section .hin-e-momint coeffi-
ci~re t .t a ziven angle of attack and flap deflection for
a 'j_:_Oc flap with an internal balance on an l.ACA 0039 air-
fcl.. 'i-e values of K are presented in figure 19 as a
fuuic tion of balance chord. Hinge-Ioment paraeters ch
sn5 chi; determined from hin.ge-mom;.,ent coefficients

obtained: by equation (1) are presented for various lengths
of i-.-iern-al balance in figure 12.









K.DAr A, T~~ 'oC. L3201'


he, results of tests of an I'AC 0009 airfoil with
a Q40-.ercent-chord flap having various arrangements of
overang and noso shane indicate the iollowi~ng conclusions:

1. The slon3 of 'he 1'ft-coeffic int curve was
arprox. catel c- the sa-ie for all sealed-ae onditicns
regardless of aercod aic-balace shape or length,
except for the elli ticai-nos3 overhang with a 50-percent-
flap chord for which the slop was a oct 5 rercnt larger
than the avere. Uneceal l thie ap reduced the slope
i percent for the fla- vwitn ala-n cv rha n and 13 to
17 percent for the flan with a::rodya CL7aic balances.

2. ,, cane in 7ift ith: fla? Deflection increased
with sealiln of the flap ~'p and :'.ith changing of the
nose shacs frnc. elliptical to blrc-t.

35. Inseuaii. the flap anp (e-c pt for the niain
.fl.ap), increasing th baace aIc le:- .. and changin the
nose shaee fron lliotical to 0blt::nit ds the rate of
chanti of: flap i oent ;'ith flap d'eflection (at
small flap defle.ctionzs) an2. z With aL.;-: Ie of attack more
posit-ve (or less. ne- tive).

4. With gap either sealed or unsMsaled, so're over-
balance was fc-d on the 50-rercent-chord blunt-nose
O -ve rang.

5. le-n the lift was varied by changing te an .:le
of attack at zero flan deflect'on, the center of lift
was at the 2),-n ecent-chcrd state. on (0.21.c) for all
overh~lagst testd th gar sealed.

6. The c~-nter of l'ft due to flan deflection and
that due to angle of attack ,l nerally _.ovaed rear.;ard as
the gap was unsealed.


Langley Temorial Aeronautical Laboratory
National Advisor Co-r.nittee for Aeronautics
Langley v191 I, Va.










NACA ARR :o. L0C01


RE 7SRT"CSS


. 'nzinger, Carl J., and Harris, '''omas A.: The Vertical
Wind,. 11.iel of the National Advisory Conuittoe for
Aeronautics. NACA Rep. No. 387, 1951.

2. Sears, Richard I., and Hogard, H. Pa Tuinnel Investigation of Ccntirol-Surface Charac-
teristics. VII A Medium Aercdyuia!a.ic Balance of
Two Nose Shapes Usd with a 0-Per cent-Chord Flap
on a NACA 0015 Airfoil. NACA ARR, July 19R2.

5. Swanson, Robert S., and Toll, Thomas A.: Jet-Boundary
Corrections for Reflection-Plane Yodels in Rectan-
gular Wind. Tunnels. NCA 'A'e :o. E22, 143.

4. Rogallo, F. M., and P-rser, Paul ".: i i.-Tunnel
Investigation of 20-Percont-Chord Plain and Frise
Ailerons on an TNACA 25012 Airfoil. NACA ARR,
Dec. 19i1

5. Swanson, Robert S., and Gillis, Clarence L. : Limita-
tions of Lifting-Line ThBory for Estimaticn of
Ailercn F inCe-Moment Characteristics. II.ACA
CB Fo. 35,02, 1OL5.

6. ATies, Milton B., Jr., and Sears, ichard I.: Deter-
mination of Control-Surface Characteristics from
V;-.CA Plain-Flap and Tab Data. NACA Rep. No. 721,
1941.

7. Ailes, T:ilton B., Jr.: Wind-Tu.nnel Investigation of
Control-Surface Characteristics. III A Small
Aerodynamic Balance of Various Nose Chespes -sed
with a 50-Percent-Chord .lap on an 7;'..A 0009 Air-
foil. NACA ARR, Aug. 1941.










T-A..A A77 Yo. L5C01 1

TABLE I

ORD TATT3 FOR ITACA 0009 LIRFOIL

stationss and ordinates in percent of airfoil cho2dc

Crdinates
Station
'Tplear Lower
surface surface

00 0
1.25 1.42 -1.42
2.5 1.96 -1.70
5.0 2.67 -2.67
7.5 3.15 -3.15
10 .51 -3.51
Si01 -1.01
20 O ; 50
25 -
30 .5 -4.50
40 .,5 ,.
50 3.97 .C7
6o 5.42 _2
70 2.75 -2.75
70 -P
0 1.7 .7
90 1.09 -1.09
95 .60 .
100oo (.10) (-.10)
100 0 0

L.T. radius = 0. j
1-____________________________ _____________________________


A;'TI07 L ADVISORY
CO" ITTEE COR AT~iOn'AUTICS













TABLB IT

STATIC 3 A-ND ORDT::-T: OR ELLIFTICALT- OSE

0.35Cf and 0.50cf OVj-iRKAiG

ritations and ordinates are in per-cent chord; stations
measured from leading ec'ge of oveirhan,,

0.35cf overhang 0.5ocf ovsrhang

Station Ordinate Station Ordinate


.03
.10
.20
.5*

.70
1.008
1 .L
1.035
2 .51
2.97
5.53
4.31
5 .26
6.47
8.21
11.63
1.01


.21




1.25
1.67
1.8
2.03
2.29
2.50
2.71
2.92
3.12
3.33
3.49
5 .42


.03
.11
.-5

.70
1.02


I ,bl
1 0 .




1 6
2. O



15.72
20.00
20.00


.21
.12
. 2


1.25
1 .46
1.67
1 .88

2.08
2.29
2.50
2.71
2.92
5.12
3.53
5.5\
5.-2


NATIONAL AD VI SOIY
CC'" iTTE. FOR AEO"'.TTICS


-- .


"'."A .., No. L5C01




















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NACA ARR No. L5C01 Fig. 1




rU







to X g
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-/



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. o4
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*2~~~ -^^^-7-----


47!/ jj
,.7 -/ t / --


I/ I Vi


/r 1


--8
- A
'' /
-' -' .


- -7


An le of at FOR a EN oTICS
Angle of attack, oco, de9


Fgure 2 4ero dynamic sec-/b? charac/fer/sf/cs
,'f oa //AC,40 0009 oaifo// /'t/ Q 0.40c p/o/i7
f/op. Flap qap, 0.005'c ; tab, O.20cf; tab qap, a0o/c;
bt = 0


6f
(deq)
o 0
S5
a /O

v20
325
-30


1 I Ihd/ll 11117111..1111r


Fig. 2








NACA ARR No. L5C01


I



.-




.q
U



O
- c
0 <


OI
o -1

0 -20



Q)
~u 28


-20 -/6 -12 -8 -4 0 4- 8 /2 /6
Anqle of attack, cco, deg
F-gure 2 .- Conc/aded.


Fig. 2 Cone.






S NACA ARR No. L5C01


(deg) '' / I



I
----^-I ---- -x


/ ,



- .-- / i


(deg)


S/0

'20
o Z
< 30


il Et -O 1E A-I ER N UT
SOMMilfEE FC AERINAUTKC


-20 -16 -.2 -8 -4 0 4 8
Angle of attack, oc,., de9


/2 /6


Figure 3. Aerod.nrm/'/c sect/o, character/t'ce
0of oan 4//CA 0009 a/'/ /ra- o0 40c P/oy/7
f/op. F/ap 9aq sealed; tab, .20 c, ; tab qap,OOO/c;
6, = f.


-A- I


Fig. 3


A / V I


/







NACA ARR No. L5C01




0




q) -
K--- 0 -

o

o .122
S.0 ---





0 ---


S --?








R --

-4^


Fig. 3 Cone.


Angle of attack, -oo, deg
-ure 3. -ConcluNded. ANALAVISO
Fl~ur& 3. -Concluded(. COMMMfTE FOR AERONAUTIC


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






NACA ARR No. L5C01


i. -




12 6 R",i




40






COIMTE FOR E




-2 0 -6 -/2 -- -4 0 4 8 /- /6
o 9 fo/ /h






gl hr r h bunt nose.



ap ap ca; oac
6 a / o b
=8 ^ -- tt-OT-- --







-z2 -/s -12 -8 -rl 0 8 /Z 16
Angle of attack, 7o, deg


Fig. 4








Fig. 4 Cone.


NACA ARR No. L5C01


9 -




00

1z
Z- <.


0 -.04



o J



o0 2


S-24
0(1
U -20
(IO

- -
ci .


-20 -/6 -/2 -8 -4- 0 4 9 /12 /6

Angle of attack, cco, de9
Sre 4. Co c/d e NATIONl ADSOiRY
/-//_ 4. Co / COMMiTnEE FOR AEONAUTnCS







NACA ARR No. L5CO1


Si--Thtl it i '
1-----









II I I 6


___0 -



/0
.4 a -- __ ,







720
} /oi-,,o-
-8---- ____




--f NATIONAL DVISO Y
C MMITT FOq AEROI AUTIC$


-/6 -12 -8 -4 0 4 8 /I2 /6


Angle of attack, oc., deg
Flaure 5 .-Xerod6/nam/c sec 'o choraccter/slcs
of an7 /ACA 0009 a/fo/'/ '/ti a, 040c
f/a/p h/av/r7g e 0.35c,~ overhang v~/-h blunt nose.
F/ap gap sealed; tab, O.8Oc; tab qap, 000/c; 50t *0


4-1










.0
Q)


Fig. 5









NACA ARR No. L5C01


U
,j



















4-1


0
'U








4_j
u
Q1

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o
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0 Q)

OS

U U


F5yure 5. -Concluded.


C NATIONAL ADVSORN
COMMITTEE FOR AERONAUTICS


-20 -/6 -/2 -8 -- 0 4 8 /2 /6
Ang/7e of gfackcco deq


Fig. 5 Cone.






NACA ARR No. L5C01


I.Go -I L






< I -I I -I ,
---- (de- -q)-



I A
-t5 / ,--
--- -- 4- 1--


T INAL AOVIS RT Y
S)MMl *EEFO !AERO (AUTCI


0 /0

0 2.


20 -/6 -/2 -4- 0 4 8 /2 /6
Anqle of attack,OC deg
F/lure 6.-Aerod, /ncamiy c sec~/b' charccterisfhc
of /A/4CA 0009 T/i/o/ wM/h 7 0.40c
I/ap hoa77q a7 O0.(3c, overhang w/fh? e///o7ia/
nose. F/ap ga, 0.005c ; tab, 020 c,; tab qap, 000/c;
=00


I v
\tj !/"t
--./ -! I ,,- --
:=~.:^./ /:=^


Fig. 6








Fig. 6 Cone.


NACA ARR No. L5CO1


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

Angle of attack, oco, deg
NATIONAL ADVISORY
F y" 6 .-ConC/ue/dd COIMITTEEFOR AERONAUTCS


ON C





*U
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I
42
0


C








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o
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NACA ARR No. L5COI


I..


I,


.6

..4

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_ 2
o
0-


4-
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S-.6
4 -6


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


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(deg) / / /
A / i / /,



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C MMI TE FI AER.UTI
",_Z_7 / + 20_



- yI?- -UI.
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4 8 /2 16


Angle of attacK, cr, de9

Fgfre 7. Aerod/amic sect/orn ch arac terX/sh
of An/ //4C, 0009 7/lfo,// //h Ca C 40c
,/ ,c /'//no O.C3J5c 2 oerh/w1n wth/j
e//pf/c / /nose. cF/ap gap sea/ed; tab, 0.20 c,;
ta/b ap, C0 00/c; S6, = t


Fig. 7


'''









NACA ARR No. L5C01






z





OU )






o .08


.04-



O D --


0 0
O -.04






u -R _06
()












O .06---
i:








,o


Fig. 7 Cone.


-20 -16 -/2 -8 -4 0 4 6 12 /6

Angle of attack, c, de9 ,NATONAL A
So a ac COMMITTEE FOR AERONAUTICS

F/qure 7. -Conc/uded.


:*







NACA ARR No. L5C01


/2-i- --- --j-- -i--- -- -- -- -i-

1.__- Z_
// / \
10----- ------- 1"'- -
-I .8------------- ----- -
,o
< / i i
u 6t



S.6--de(deg)
o '/ / /






-20 -6 -/ -8 -4 -4 -- -









Angle oI attclc, oco, deq

oa1 ## cA 0009 kvl)- h a -. 4-0 c/o-
- /-









o q a O.-Oc, rhany wh un ose.

Fap gap (dtab, 20_c I
0 / 001
t---- -- f
. -.4 1 -lo. _






COl IMInl FOR tERON ,TICS
-20 -/6 -/2 -8 -4 0 4 8 /2 /(
Angle of attack, oc0, dec)
/7..ure 8. -,!ldrodfyno ml'c seci/on characters t,/s
of ev a4 hyil/q o" O.JOcf o/iero'n9o w/i/7 bl/-nrt ose.
F/ap oap; 0005c ; tab, 0.20of ; tab gap/, O0.0/c ;
t :0.


Fig. 8








NACA ARR No. L5C01




OI

0hF ---T
*4.. -----









.u









4.4
.o4--
^ .o



(U 0
i u-

S ...6


^

Fig. 8 Cone.


-20 -16 -12 -8 -4- 0 4- /2 /6

Angle of attack, coo, deg

F/2ure 8. Concluded.







NACA ARR No. L5C01


.8 l"
I, /

80-
S.2----- ----
S.I----





(deg)

S 7 Z Z ( J I/I o




^o == ====== =


-1/2


mna UNa RL U
AM1 I F~HiIRO. IU_
-20 -/ -/2 -8 -4 0 4 8 /2 /6
Angle of attack, oco, deg


F/lure 3.--erody/7om/ic ect/'o chorocferi-/'cs of
an /4 CA 0009 a/rfo/7 w 7 O.C40c / /op ',I7
a J-Oc6 overAe/7n w b/ jb/u nt noFse. F/ap aoap
.seo/edi ab, O.2Oc, ; tab qap, .0/c; 6t0.


Fig. 9








NACA ARR No. L5C01





.10s ---

^0---



0 -
U) .


k J


.16

.12.--

.08-
Q) --


o .04
-.04--



0 -08
/ ---
)a

R 16


Fig. 9 Cone.


-20 -16 -/2 -8 -# 0 4 8 /2 /6

Angle of attack, oco, deg

F






NACA ARR No. L5CO1


1.-



If


.8
i.6


.4
S.2,
o


S ..




-6




-IS


S ,,








_7-






S 'eq)
S/ / /o



/ 5
C -- -- --EE F01 A-.- I- -
/ !-- /- ---




I /MMIT EE FO_ AER AUTIC


-20 -/6 -/2, -8 -4


0 4 8 /Z /6


Anq/e of attack, oc deq

/,Ure /0 .-,4erodoyamic section characfer i'tcs
of an/ A4C, 0009 o~rfoi/ with ao O.40c f/ao
hoer/? o 0.JGOc, overhang with elliptical nose.
Flap gap, 0O005c; tab, O.20 c, tab pqap, 0O0/c;
6.-~O0.


Fig. 10








NACA ARR No. L5C01







S 0
.h--




.04 -
Q)









U 0 -/-











to
t) --I
.12--






Q)









c -OQ:


Fig. 10 Conc.


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

Anqle of attack, Cco, deg

F/ure /0 -Concluded.








NACA ARR No. L5C01


LO


1)
'I-
Q)
0

U
-S








U
(^


Q)





0


1.4


/41




.8 -- --4







.2-



-- /





-- --------------/
CO1MtT 1OR / 5O
--- /7'- /5






.I P

-io
_0 /- / -
- ------ /--/--o-------- o







-Z NTI iAL O )VISOR S
COl MITTE FOR tON JTC


-20 -16 -/2 -6 -- 0 f 8 /2 /6

Angle of attack, o. de9

Figure II. -Aerodyrnymic sech-bon choracter/-'f/cs of
/n /A6A 0009 airfoi/ w/t/' a 0,4dcf/ SO.JOc, 2erhang wi/h ell/I'//'al nose. Flap
gPo sea/ed; tab, 0.20c ; tab gap, .OO/c ; 5tO


Fig. 11








NACA ARR No. L5CO1




I
Ch




o, -









.04

s% s -0
I:: ----


Fig. 11 Cone.


-20 -/b -/2 -8 -i9 0 8 /2 /6

Angle of attach, ao, de9

rY/ure //.-Concluded.









NACA ARR No. L5CO1


4..


Fig. 12






*o.





oo









.4
U


i













'1








10
C>







NACA ARR No. L5C01 Fig. 13


.28
0

o .26------------------t----
U .26



I. .22-
F/lap gap sealed
S.20 F---l---Fap qap, 0005c

.i .18 -OCo
.2 -_ _rye __4_ ^

./6 --- -8 --
S./o -8--- --_----





.08 ,___
aU -- -


O ---- /-- --
o .08


.02 --
I /


_o _i /,

I NATIO AL Al VSON
0 -- _-- | CO- M-TE FOR A CS
0 4 8 12 /6 20 24- 28 32
F/ap deflection, 6., deg
F/qure /3.- Increment of airfoil section profi/e-drag
coefficient caused by deflection of a 0.40c pain
flap with flap qap sealed and widh f/ap qap v005c -
Tab, 0.20 cf; toa. gap, 000/c; 65t0.







NACA ARR No. L5C01


-4 0 4 6 /2 /6 20 24 28 JZ
F/aop odef/ect/on, f deg
/,gure /4.-Zncrrement of a/'lofl/ secb/on profi/e-drqa
coeff/cient cosed b/ dy ef/ec/y"oe of 0. Oc //op
haiv/7g a O.3J6cf, A//unl overha/o wifh f/ap qap
sealed and with flap qap,OOO5c. Tab, 020 cf; fab
gap, 000/c; 6t= .


Fig. 14







NACA ARR Ho. L5C01


~.*; /---------------------


0------------------------------*------ 0



1 .04 -de W /,' -- -
S./O




MI EE FO AERO MTI





Fapo def/ec!/n, 6ode9





gap, 0.00/c; .
"~i ~pNA14EO I ENAL A I


-4 0 4- 8 A2 16 M20 24- 28 32


Figure 15--.Z-nckremen?0/" o'iol/ sec/-ion prolle-dr&g
coef7l;ien- caused by del/ec~l-bn of 0. 4Oc A/op
h1ayln7 a O. 50cc blut overhan9 with flap ?ap
sealed and wilh flap 9pap O.O6c. Tab, 0.20 cf ; tab
qap, O.O0cC; OtO=0


Fig. 15







NACA ARR No. L5CO1


(de/ r
2/














I A
----------------------------------- ^--^ --- -
S/ 0\
1.4---------------^-- r- --













4-
-4-p-- .- --Z -





-- -4-
/ /
-- ,.-,, / / I











6 / /O
'-, _/-_


-/ -

--/ -y---








S20
30
g ------ ------/----- --0




SNATI/L ISORY
I p _COM ITTEE FOR f IRONA TICS


-. -6
-20 -16


-/1 -8


-4 0 4


Angle of attack, oro, deq
Figure 16 -,4erodyn7am/c decf/ok character/Af/cs oc'fo
/VAC,4 0009 al/ro// w//7 ( .40 c p/a/n /a/p h/>aiz7y
a O., p/aO/C ,rb w0/~0h0 / -/, /. /C/ap yo/p S ei/ed-
-fob gap, 00/c.


Fig. 16


8 /2


-/








NACA ARR No. L5CO1





I

C,'
00


/-----


OO




FI--
[ u





0") ---_,






F -.0




Q, 8 --. 24









S- _66
-:24 N





ci 6 _


Fig. 16 Cont.


-2O -16 -I/ -8 -4 0 4 8 1/ /6 0Z


Anqle of attack, oCo, deg

F/L7ure /6.- Coni/n ued.








NACA ARR No. L6C01






.20 I-I---I


4.:
C'
q,


4j
I











QI

Q)
.Q


.08

.04

0

-04

.08


-16

._20


32Z


Fig. 16 Cone.


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

Angle of attack, oco, deg

F 'ire /6 .-Conc/uded.






NACA ARR No. L5CO1


k"






IN
IN


S-0o -/ -/ -8 -4 0 48 /8 /6
Angle of afttcck YCcdeg
F -ure /7. Aerodoynom/c sectobn characfer/istic of
on /VA4CA 0009 airfol/ wl'fh a 0. 40c //%ap havI/
a 0. 35o overhang w/,h el///pofc/ nose a70nd
hav/n9 a o/a/, tarb //'h F/op oap seed;
tab 9ap, 0.00/c. 6


Fig. 17





















I
NACA ARR No. L5C01








I .





.1

.08----




I s I
I- J0- --





os | ~ j 321o6 1


Fig. 17 Cont.


-20 -16 -/8 -8 -4 0 4 8 12 16
Ang/e of affcyc/r, cVo, de


/O-ure /17. Conf/ued.








NACA ARR No. L5C01


'3





0

-k








.0
o
<3


-20 -/6 -12 -6 -4 0 4 8 /1 /6
,4np/e of att--c/, ajo jey

/1adre /7.- Conc/aded


Fig. 17 Cone.





iiI
F-




S NACA ARR No. L5C01 Fig. 18







2.5










0 ,,' ---



.2-
i ,' /C /






30/


.2


0 '










-20 -6 -/2 -8 -4 0 4 / /6
Angle of attack, cK,, de9
.ure /6.- Variation with an/e of attack of resultant
pressure coefficient aci-ass the nose seal of a l40c
p/a/* f/a, on a, 4'ACA 0009 airfoil. 7ab, O.ZOcf
tab qap, 0. 00c ; 6, = 0







NACA ARR No. L5C01


C)


Fig. 19


= -v

,L;) /zI Y








UNIVERSITY OF FLORIDA

3 1262 08106 553 3




ULi DIVERSITY" OF FLORIDA
rOUMIE NTS DEPARTrJMENT
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