PRESSURE DISTRIBUTIONS ON A WING HAVING NACA 4415 AIRFOIL SECTIONS WITH ...

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N A S A TECHNICAL
MEMORANDUM
PRESSURE DISTRIBUTIONS ON
A WING HAVING NACA 4415 AIRFOIL
SECTIONS WITH TRAILING-EDGE
o0
FLAPS SET AT AND 400
by Arthar W, Carter
Laagley Research Center
Humpton, V 23365
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
: . .r"" ;I,,::.
-8 -. L8d.8 K.
I I
NASA TM X-2225
4. Title and Subtitle 5. Report Date
Arthur W. Carter
10. Work Unit No.
9. Performing Organization Name and Address 721-01-11-01
NASA Langley Research Center
11. Contract or Grant No
Nampton, Va. 23365
Period Covered
ernormdurn
National Aeronautics and Space Administration
:ode
Washington, D.C. 20546
15. Supplementary Notes
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16. Abstract
An investigation has been made in the Langley 300-MPN 7- by 10-foot tunnel through
a range of free-stream dynamic pressures and through a range of angles of attack to deter-
mine the chordwise pressure distributions on a wing having NACA 4415 airfoil seelions wlth
flaps set at O0 and deflected down 40'. The unswept, untapered wing had an aspect ratio of6
and full-span 30-percent-chord slotted flaps.
The results of the investigation are presented as curves of chordwise pressure dish-
butions at the 25-percent-semispan wing station. Tabulated pressure data are alsl3 presented
as well as the longitudinal aerodynamic characteristics of the model corresponding "c the
pressure data.
-
17. Key Words (Suggested by Author(s)) 18. Distribution Statement
Pressure distributions Unclassified - Unlimited
NACA 441 5 airfoil
Trailing-edge flaps
Unclassified Unclassified 7 3 - $3-00
For sale by the National Technical Information Service, Springfield, Virginia 221 51
PRESSURE: DISTRIBUTIONS ON A WING a V m G
NACA 441 5 AIRFOIL SECTIONS WITH TMILING-EDGE FLAPS
SET AT 0 ' AND 4O0
By Arthur W. Carter
Langley Research Center
An investigation has been made in the Langley 300-MFB 7- by 10-foot LiunneQt hrough
a range of free-stream dynamic pressures and through a range of angles of attack to deter-
mine the chordwise pressure distributions on a wing having NACA 441 5 airfoil sections
with flaps set at 0 ' and deflected down 40'. The unswept, untapered wing had an aspect
ratio of 6 and full-span 30-percent-chord slotted flaps.
The results of the investigation are presented as curves of chordwise pressure dis-
tributions at the 25-percent-semispan wing station. Tabulated pressure data are also pre-
sented as well as the longitudinal aerodynamic characteristics of the model corresponding
to the pressure data.
INTRODUCTION
A wind-tunnel investigation of the jet-location interference effects on the longitu-
dinal aerodynamic characteristics of a jet V/STOL model has been made for an unswept,
untapered wing with an aspect ratio of 6 and 30-percent-chord slotted flaps, Aerodynamic
force and pitching-moment measurements for this wing are presented in reference 3. In
order to supplement these data, additional aerodynamic and pressure-distrib~~tiomne a-
surements on the wing are presented in the present paper for the wing in the basic eardig--
uration (zero flaps) and with the Fowler-type full-span flaps deflected down 40"- Pres-
sure distributions on the NACA 4415 airfoil section have been presented in reference 2 at
Miach nurnbers from 0.3 to approemately 0.85.
SYMBOLS
The physical quantities in this paper are given both in the International System of
Ynit~( SI) arid in the U.S. Customary Units. The measurements and calculations were
made in the U.S. Customary Units.
Drag
adrag coefficient,
q ,S
-Lift
lift coefficient,
(3 s ,
Pitching moment
;pitching-moment coefficient,
s,Sc
pt,w - pz
pressure coefficient,
s,
a:laord, meters (feet)
I.ocal static pressure, newtons/meter2 (pounds force/foot2)
free-stream total pressure, newtons/metera (pounds force/foot2)
free-stream dynamic pressure, newtons/meterZ bounds force/foot2)
wing area, meters2 (feet2)
longitudinal distance from leading edge of wing or flap (posliLive when
measured aft of leading edge of wing), meters (feet)
angle of atbck, degrees
flap def lection (positive when deflected down), degrees
MODEL ANI) APPAlRATUS
A drawing of the model is shown in figure 1. The wing was unswept, ua~tapered,a nd
had an aspect ratio of 6 with a 30-percent wing-chord slotted Fowler-type flap defleczed
40~.T he flap was removed from the wing for the zero-flap or basic config~uration, The
wing and flap both were constructed with NACA 4415 airfoil-section contours, The wing
was mounted with the top of the wing at the top of a cylindrical fuselage whic1.e had a faired
nose section. The wing was set at zero incidence relative to the fuselage. lin order lo
determine the chordwise pressure distributions on the wing and flap, pressure orifices
were located on the upper and lower surfaces of the right wing and flap at the 25-pereen:-
semispan station. Measurements of the pressures were obtained by the use of pressure
transducers.
The model was mounted on a sting-supported six-component strain-gage balance
for direct measurement of the total forces and moments on the model as sho~~aiinn figure 2,
The balance was located at the center of the fuselage with the moment center of the balance
located at the 25-percent-chord station of the wing. An electronic clinometer was located
in the nose section of the fuselage for use in determining the geometric angle of attack of
the wing during the investigation.
TEST CONDITIONS
The investigation was made in the Langley 300-MPH 7- by 10-foot tunnel. The
Reynolds number based on the maximum free-stream dynamic pressure of 287% ~/r;-,z
(60 lbf/fta) and wing chord of 0.2032 m (0.667 ft) was 0.9 X 10~.
Aerodynamic and pressure data were obtained for the wing with flaps deflected
down 40' and for the basic wing (flaps zero). The data were obtained at a constant geo-
metric angle of attack of approximately for a range of values of free-stre;arn dynamic
pressure from 0 to approximately 2873 N/m2 (60 lbf/ft2). Data were also olotained
through a range of values of angle of attack at constant free-stream dynamic pressures
of approximately 420, 1020, and 2840 N/m2 (8.8, 21.3, and 59.3 lbf/ft2).
PmSENTATION OF DATA
The nondimensional pressure coefficients were normalized to the tunnel free-stream
dynamic pressure. No corrections were made to the data for model blockage or wilqd-
tunnel boundaries. No corrections or adjustments were made to the longitudinal drag
coefficient CD for the base drag.
The data are presented as indicated below without analysis or discussion:
--
11 Type oi data of wOfi nagt,t ack Flap deflection, dyFnarmeei-cs ptrreeasmsu re Table Figure
dee:
I-- deg ~/m2 1bf/ft2
- -
1
Pressdrt distribution =O 0 185 to 2847 3.863 to 59.458 I
tab~l~liori -4.94 to 20.34 0 420 8.8 II
-5.01 to 20.59 0 1020 21.3 III
I
-5.10 to 21.22 0 2840 59.3 N
=O 40 217 to 2320 4.535 to 48.461 V
-4.80 to 14.33 40 420 8.8 VI
-4.61 to 12.73 40 1020 21.3 VII
40 a2840 59.3
Stallc ~o~igitudinal / =O 0, 40 0 to 2873 0 to 60 3
I srability -5to21 0, 40 420 8.8 4
1 1020 21.3
2840 59.3
-- -- --
rcssurc distr~bL~lo n =O 0 185 to 2847 3.863 to 59.458 5
-4.94 to 2.02 0 420 8.8 6 (a)
3.07 to 10.23 0 420 8.8 6 (b)
11.28 to 16.38 0 42 0 8.8 6 (4
17.36 to 20.34 0 420 8.8 6 (4
-5.01 to 2.11 o 1020 21.3 7 (a)
3.13 to 10.40 0 1020 21.3 7 (b)
11.46 to 16.58 0 1020 21.3 7(c)
17.58 to 20.59 0 1020 21.3 7 (4
-5.10 to 2.34 0 2840 59.3 8 (a)
3.43 to 10.95 0 2840 59.3 8 (b)
I 12.00 to 17.15 0 2840 59.3 8(c)
18.15 to 21.22 0 2840 59.3 8 (4
I =O 40 217 to 2320 4.535 to 48.461 9
-4.80 to 2.17 40 420 8.8 lob)
I
3.18 to 8.28 40 420 8.8 lob)
I 9.33 to 14.33 40 420 8.8 10( 4
-4.61 to 2.55 40 1020 21.3 11 (a)
---I 3.56 to 8.75 40 1020 21.3 lib)
9.74 to 12.73 40 1020 21.3 ll(c)
40 a2840 59.3
"Ehir,rg the lnvestlgation of the wlng wlth flaps deflected down 40' at a free-stream dynam~cp ressure of 2840 ~ / (m59.3 ~lbf/ ftq, the
gressLres over a large portion of the chords of the wlng and flap exceeded the limits of the data-acquisition system, and these pressure data,
rhel efore, are lot ararlable.
Eangley Bsez~rchC enter,
National Aeronautics and Space Administration,
Nampton, Va., March 24, 1971.
REFERENCES
1, Carter, Arthr W.: Effects of Jet-Exhaust Location on the Longihtdinal Aerodynamic
Gharact~eristicso f a Jet V/STOL Model. NASA TN D-5333, 1969.
2, Graham, Donald J.; Nitzberg, Gerald 33.; and Olson, Robert N.: A Systematic Investi-
gation of Pressure Distributions at High Speeds Over Five Represenktive NAGA
Low-Drag and Conventional Airfoil Sections. NAGA Rep. 832, 1945.
PRFSSURE DISTRIBUTION ON 4415 WING
ALPHA = -310 DEG DYN4Y IC PRESSURE = 3.863 LSFfSQ.FT. FLAP = 0 DCG
WING UPPER SURFACE WING LOWER SURFACE
XfC C'P XfC C'P
0.0000 -0326 0.0300 -3176
.0050 .2442 .075? .5861
.0100 .6350 .010n .8466
-0175 -5141 .Ol75 1.05R3
,0500 1.5142 .0500 1.4653
.0750 1.3677 -0750 1.4328
-1000 1.5305 .17nn 1.4165
.ZOO0 1.8561 -2000 1.2RC1
.3000 1.9050 .??no I. 164~
-4000 1.8235 .47n0 1.13P2
-5000 1.7421 .5000 1.0764
,6000 1.6282 .6?00 1.0648
.7000 1.5793 .7nOn 1.0341
.BOO0 1.2374 .87f'0 1.0077
-9000 1.0420 .9nco .9265
1.OPOO 1.4165 1.00"P 1.4165
ALPHA = -020 OEG DYNAMIC PRESSURF = R.876 LBF/SO.FT. FLAP- O OtL
WING UPPER SIJRFACE WING LUHER 5UKFACF
X/C c'P XfC P'c
ALPHA = .050 OEG DYNAMIC PRESSURE = 15.5C1 LRF/SO.FT. FLAP = C DtG
WING UPPER SURFACE WING LnWE4 SIJRFACE
Note: The conversion factor from pounds force/square foot to newtons/square meter is 47.880258.

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TABLE I. CONCLUDED
PRESSURE OISTRIBUTInN 0N 4415 WING
ALPHA = -160 DEG DYNAMIC PRESSURE = 48.733 LSF/SO.FT. FLAP = n OF<
WING UPPER SURFACE WING LOWER SURFACE
ALPHA = .200 OEG DYNAMIC PRESSURE = 59.458 CSFISQ.FT. FLAP = c i>tr,
WING UPPER SURFACF WING LOWER SURFACF
TABLE I1
PRFSSURE OISTRIBUTION ON 4415 WING
ALPHA = -4.340 DEG DYNAYIC PRESSURE = 8,821 LSFISQ-FT. FLAP = 0 OEG
WING IJPPER SURFACE WING LOWER SURFACE
ALPHA = -4.347 CEG DYYAY IC PRESSIJRE = 8.766 LRF/SQ.FT. FLAP = D DEG
iJIClG LJPPER SURFACC WING LOWER SURFACF
b1P1iL = -2.990 1'6 OYN4MIC PRESSUKF = 8.807 LRF/SQ.FT. FLAP = 0 DEG
W Ir NG IlPPFR SURFACE WlNG LOWER SURFACE
:!late: The conversion factor from pounds force/square foot to newtons/square meter is 47.880258.