NASA-TM-X-2225 · Pressure distributions on a wing having NACA 4415 airfoil sections with trailing-edge flaps set at 0 deg and 40 deg

A T E C H N I C A L

N A S

M E M O R A N D U M

PRESSURE DISTRIBUTIONS O N

A WING HAVING NACA 4415 AIRFOIL

SECTIONS WITH TRAILING-EDGE

FLAPS SET AT o0 AND 400

by Arthar W, Carter

Laagley Research Center

Humpton, V 23365

N A T I O N A L A E R O N A U T I C S A N D SPACE A D M I N I S T R A T I O N

: . . r"" ; I , , : : .

8 L 8 d . 8 K.

- -.

NASA TM X-2225 I I

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

-

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 a t O0 and deflected down 40'. The unswept, untapered wing had an aspect ratio o f 6 and full-span 30-percent-chord slotted flaps.

The results of the investigation a r e presented a s curves of chordwise pressure d i s h - butions a t the 25-percent-semispan wing station. Tabulated pressure data a r e alsl3 presented a s well a s the longitudinal aerodynamic characteristics of the model corresponding "c the pressure data.

- 17. Key Words (Suggested by Author(s)) 18. Distribution Statement

P r e s s u r e 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 LiunneQ 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 441 5 airfoil sections

with flaps set a t 0 ' and deflected down 40'. The unswept, untapered wing had a n aspect

ratio of 6 and full-span 30-percent-chord slotted flaps.

The results of the investigation a r e presented a s 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 a r e presented in reference 3 . In

order to supplement these data, additional aerodynamic and pressure-distrib~~tion mea-

surements on the wing a r e 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-

s u r e 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 a r e given both in the International System of

Y n i t ~ ( S I ) a r i d 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 a t b c k , 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, and

had a n aspect ratio of 6 with a 30-percent wing-chord slotted Fowler-type flap defleczed

4 0 ~ . The flap was removed f r o m the wing f o r the zero-flap o r basic config~uration, The

wing and flap both w e r e 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 s e t at z e r o incidence relative to the fuselage. lin order lo determine the chordwise p r e s s u r e distributions on the wing and flap, p r e s s u r e orifices w e r e located on the upper and lower surfaces of the right wing and flap a t the 25-pereen:- semispan station. Measurements of the p r e s s u r e s were obtained by the use of pressure transducers.

The model was mounted on a sting-supported six-component strain-gage balance

f o r direct measurement of the total f o r c e s and moments on the model as sho~~ain in 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 f o r u s e in determining the geometric angle o f attack of the wing during the investigation.

TEST CONDITIONS

The

The investigation was made in the Langley 300-MPH 7- by 10-foot tunnel.

Reynolds number based on the maximum free-stream dynamic p r e s s u r e of 287% ~ / r ; - , z (60 lbf/fta) and wing chord of 0.2032 m (0.667 ft) was 0.9 X 1 0 ~ .

Aerodynamic and p r e s s u r e data w e r e 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 O F DATA

The nondimensional p r e s s u r e coefficients were normalized to the tunnel free-stream

dynamic pressure. No corrections w e r e made to the data f o r model blockage or wilqd-

tunnel boundaries. No corrections o r adjustments w e r e made to the longitudinal drag

coefficient CD f o r the base drag.

The data a r e presented as indicated below without analysis o r discussion:

--

Free-stream Of attack Flap deflection, dynamic p r e s s u r e

1 Type o i data

of wing, Table Figure dee: deg ~ / m 2 1bf/ft2

I-- - -

Pressdrt distribution = O 0 185 to 2847 I 3.863 to 59.458 t a b ~ l ~ l i o r i -4.94 to 20.34 0 420 II 8.8 -5.01 to 20.59 0 1020 III 21.3 -5.10 to 21.22 0 2840 N 59.3 =O 40 217 to 2320 V 4.535 to 48.461 -4.80 t o 14.33 40 420 VI 8.8 -4.61 to 12.73 40 1020 VII 21.3 40 a2840 59.3

I

Stallc ~o~igitudinal =O 0, 40 0 to 2873 0 to 60 3

I srability / - 5 t o 2 1 0, 40 420 8.8 4

1 21.3 2840 59.3 -- -- -- 0 rcssurc distr~b~ Llon =O 185 to 2847 3.863 to 59.458 5 -4.94 to 2.02 0 420 8.8 6 (a) 0 3.07 to 10.23 420 8.8 6 (b) 0 11.28 to 16.38 42 0 8.8 6 ( 4 0 17.36 to 20.34 420 8.8 6 ( 4

o -5.01 to 2.11 1020

21.3 7 (a) 0 3.13 t o 10.40 1020 21.3 7 (b) 11.46 to 16.58 0 1020 21.3 7(c) 0 17.58 to 20.59 1020 21.3 7 ( 4 0 -5.10 to 2.34 2840 59.3 8 (a) 0 3.43 to 10.95 2840 59.3 8 (b) 0 12.00 to 17.15 2840 59.3 8(c) 0 18.15 to 21.22 2840 59.3 8 ( 4

I

40 =O 217 to 2320 4.535 to 48.461 9

I

40 420 8.8 -4.80 to 2.17 l o b ) I 40 3.18 to 8.28 420 8.8 l o b ) I 40 9.33 t o 14.33 420 8.8 10 ( 4 -4.61 t o 2.55 40 1020 21.3 11 (a) 40 3.56 to 8.75 1020 21.3 lib) 21.3 40 9.74 to 12.73 1020 l l ( c ) 40 a2840 59.3

I - - -

deflected down 40' a t "Ehir,rg the lnvestlgation of the wlng wlth flaps a free-stream d y n a m ~ c pressure of 2840 lbf/ftq, the ~ / m ~ (59.3 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 l o t ararlable.

Eangley B s e z ~ r c h Center, National Aeronautics and Space Administration, Nampton, Va., March 24, 1971.

REFERENCES

1, Carter, A r t h r W.: Effects of Jet-Exhaust Location on the Longihtdinal Aerodynamic

NASA TN D-5333, 1969.

Gharact~eristics of a Jet V/STOL Model.

2, Graham, Donald J.; Nitzberg, Gerald 3 3 . ; 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 D I S T R I B U T I O N ON 4 4 1 5 WING ALPHA = - 3 1 0 DEG DYN4Y IC PRESSURE = 3.863 LSFfSQ.FT. FLAP = 0 D C G WING UPPER SURFACE WING LOWER SURFACE X f C C'P XfC C'P 0.0000 - 0 3 2 6 0.0300 -3176 .0050 . 2 4 4 2 .075? . 5 8 6 1 . 0 1 0 0 .6350 .010n . 8 4 6 6 - 0 1 7 5 - 5 1 4 1 . O l 7 5 1.05R3 ,0500 1.5142 .0500 1.4653 . 0 7 5 0 1.3677 - 0 7 5 0 1.4328 - 1 0 0 0 1.5305 .17nn 1.4165 - 2 0 0 0 1.2RC1 .ZOO0 1.8561 . 3 0 0 0 1.9050 .??no I . 1 6 4 ~ - 4 0 0 0 1.8235 .47n0 1.13P2 .5000 1 . 0 7 6 4 - 5 0 0 0 1.7421 ,6000 1.6282 .6?00 1 . 0 6 4 8 .7nOn 1 . 0 3 4 1 . 7 0 0 0 1.5793 .BOO0 1.2374 .87f'0 1.0077 - 9 0 0 0 1.0420 . 9 n c o .9265 1.OPOO 1.4165 1.00"P 1.4165 ALPHA = - 0 2 0 OEG DYNAMIC PRESSURF = R.876 LBF/SO.FT. F L A P - O OtL WING LUHER 5UKFACF WING UPPER SIJRFACE X f C c ' P X/C c'P ALPHA = .050 OEG DYNAMIC PRESSURE = 15.5C1 LRF/SO.FT. FLAP = C D t G WING UPPER SURFACE WING LnWE4 SIJRFACE Note: The conversion factor from pounds force/square foot to newtons/square meter is 47.880258.

TABLE I . - CONCLUDED

PRESSURE O I S T R I B U T I n N 0 N 4 4 1 5 W I N G ALPHA = - 1 6 0 D E G D Y N A M I C P R E S S U R E = 4 8 . 7 3 3 L S F / S O . F T . F L A P = n O F < W I N G U P P E R S U R F A C E W I N G LOWER S U R F A C E A L P H A = . 2 0 0 O E G D Y N A M I C P R E S S U R E = 5 9 . 4 5 8 C S F I S Q . F T . F L A P = c i>tr, W I N G U P P E R S U R F A C F W I N G LOWER SURFACF TABLE I1 P R F S S U R E O I S T R I B U T I O N ON 4 4 1 5 W I N G A L P H A = - 4 . 3 4 0 D E G D Y N A Y I C P R E S S U R E = 8,821 L S F I S Q - F T .

F L A P = 0 OEG W I N G I J P P E R S U R F A C E W I N G L O W E R S U R F A C E A L P H A = - 4 . 3 4 7 C E G D Y Y A Y I C P R E S S I J R E = 8 . 7 6 6 L R F / S Q . F T . F L A P = D D E G iJIClG LJPPER S U R F A C C W I N G L O W E R S U R F A C F b 1 P 1 i L = - 2 . 9 9 0 1 ' 6 O Y N 4 M I C P R E S S U K F = 8.807 L R F / S Q . F T . F L A P = 0 D E G W I rNG I l P P F R S U R F A C E W l N G L O W E R S U R F A C E The conversion f a c t o r from pounds f o r c e / s q u a r e f o o t t o newtons/square meter i s 47.880258.

:!late:

TABLE 11. - C O ~ ~

PRESSURE D I S T R I B U T I O N ON 4 4 1 5 WlNG

ALPHA = -1.970 OEG DYNAMIC PRESSURE = 8 . 8 5 8 L R F I S Q - F T . F L A P = " O F 5

W I N G UPPER SURFACE WING LOWER SURFACE X I C c"P X/C C$ ALPHA = -1.000 DEG DYNAMIC PRESSURE = 9.849 LRF/SR.FT. FLAP = n D E G M ~ N G UPPER SURFACE WING LOWER SURFACE

X / C cb X I C cb

ALPHA = . 0 2 0 DEG DYNPMIC PRESSURE = 8.940 LRF/SQ.FT. FLAP = D t ?

WING UPPER SURFACE WING LOWER SURFPCF

TABLE 11. - CONTINUED

PRESSURE D I S T R I B U T I O N ON 4 4 1 5 WING A L P H A = 1.C30 D E G DYNAY I C P R E S S U R E = 8.849 L B F / S Q . F T . F L A P = 0 DEG W I N G U P P F R SlJRFACE W I N G LOWER SlJRFACE X / G C ' P X / C C'P n.0000 .0213 0.0000 .0213 .005C .220'1 ,0050 - 3 7 6 7 .013C .5970 .0100 . 6 3 2 6 .0175 .9951 - 0 1 7 5 -7R18 .05'30 1.4373 .0500 1 . 4 6 4 2 - 0 7 5 0 1.4855 - 0 7 5 0 1.6134 . l o 3 0 1.7982 - 1 0 0 0 1.4073 .21"0 1.9170 - 2 0 0 0 1.2368 . 3 0 3 0 1.9475 .3000 1.1495 .4nC0 1.8196 . 4 @ 0 0 1.0891 - 5 0 0 0 1;0287 .5C30 1.6916 . 6 " 3 0 1.62C6 .6000 1.0002 - 7 0 0 0 1.4358 - 7 0 0 0 - 9 5 9 9 .ROO0 1.2865 .8000 . 9 3 8 1 . 9 0 3 0 1.0733 .9000 - 8 9 2 8 1 . 0 ~ 0 0 1.1657 1.0000 1.1657 A L P l i A = 2.32: P E G D Y N A Y I C P R E S S U R E = 8.821 L B F / S Q . F T . F L A P = 0 OEG WING U P P F P S t l R F A C E W I N G LOWER S U R F A C E ALPii.4 = 3.^70 R E G DYN4Y I C PRESSURE = 8.803 L R F I S Q - F T . F L A P = 0 DEG W I N G U P P F R SIJRFACE W I N G LOWER S U R F A C E

TABLE 11. - Coi3'ITNUED

PRESSURE O I S T R I B U T I O N ON 4415 WING

ALPHA = 4.103 OEG D Y N A Y I C PRESSURE = 8.821 L B F / S Q . F T . F L A P = " OEG

WING UPPER SURFACE WING LOWER 5URFACE ALPHA = 5.090 D E G OYNAYIC PRESSURE = 8.794 L R F / S Q . F T . F L A P = O DFG WING UPPER SllRFACE WING LOWER SURFACF A L P H A = 6.140 O E G D Y N A Y IC P R E S S U R E = 8.721 L R F / S Q . F T . F L A P = c D E G WING UPPER SURFACE W I N G LOWER SURFACE

TABLE 11. - CONTINUED

PRESSURE D I S T R l B U T I O N ON 4 4 1 5 WING RLi'H3. = 7.150 O E G OYNAY IC PRESSURE = 8.766 LRF/SQ.FT.

FLAP = 0 OEG WING UPPER SURFACE WING LOWER SURFACE

X/C cb

0.00CO - 5 0 9 4 . 0 0 5 0 - 0 4 3 0 .0100 - 0 4 3 0 - 0 1 7 5 ,1148 .05CO .5596 - 0 7 5 0 . 7 3 1 8 ,1000 - 7 9 6 4 .2000 . a 3 0 1 ,3000 . 8 6 7 4 - 4 0 0 0 . 9 1 6 5 .5000 - 8 7 9 2 - 6 0 0 0 - 8 7 9 2 .7000 - 8 6 5 7 .ROO0 - 8 7 9 2 - 9 0 0 0 .a674 1.0000 1.1982 A L O Y A = 9.190 OFG DYNAMIC PRESSURF = 8.693 LBF/SQ.FT. FLAP = 0 OEG WING LOWFR SURFACE X/C c$ 0.0000 - 6 0 7 8 - 0 0 5 0 - 9 5 0 6 - 0 1 0 0 3.0000 - 0 1 7 5 ,0289 .0500 - 4 3 4 1 .0750 ,6584 .LO00 - 7 5 9 7 .2000 . a 0 6 1 . 3 0 0 0 . 8 2 0 0 .4000 .a234 .5000 . a 3 7 1 .6000 ,8593 - 7 0 0 0 . 8 6 1 0 .A000 .R644 -9CCO .R729 ~ . n o o o I .1721 I C P N G = 9.233 D E t OYNAYIC P9ESSURE = 8.730 LRF/SQ.FT.

FLAP = 0 OEG WING IIPPFQ SUQFACE WING LOWER SURFACE

X/C cb

X/C C'P r . n n n o . ~ 5 7 7 . P ? 5 q 2.2767 . ? l O Q 2.6657 . 7 1 7 5 7.9899 . 0 5 9 0 3.19RA . n 7 5 ~ 2.9511 . l n r O 2.8674 . ~ n n 7.5572 . j e n n 2.3775 ~ . n ? i 7 . 5 " 7 0 1.8278 6 1.671 5 . 7 C q 0 1.4675 . A n O O 1.1960 .9'"-l" 1.0739 1 . D C c O 1.1471

TABLE 11. - CONTDWED

P R E S S U R E O I S T R I R W T I O N O N 4 4 1 5 W I N 6 A L P H A = 10.230 D E G D Y N A Y I C P R E S S U R E = 8.7?2 L R F / S Q . F T . F L A P = 0 ntc7 W l N G U P P E R S U R F A C E W I N G L O W E R S U R F A C E ALPHA = 11.280 D E G DYNAY I C P R E S S U R E = 8,7?2 LBF/SQ.FT. F L A P = f\ ntci W I N G U P P F R 5 U R F R C E W I N G L O W E R S U R F A C F

X / C C'P X / C cb

0.0000 1.4094 c'.0000 1 . 4 0 9 4 - 0 0 5 0 2.9778 .DO50 .44/11 .0100 3.3826 . o i n n . I P ~ Z - 0 1 7 5 3.5705 - 0 1 7 5 ,7434 . 0 5 0 0 3.6139 - 0 5 0 0 - 2 6 3 7 - 0 7 5 0 3.2308 .3750 . 4 3 3 7 . I 0 0 0 2.9973 . l o 0 0 . 4 7 7 0 - 2 0 0 0 2.7538 .2000 - 6 7 3 7 - 3 0 0 0 2.4791 .3qno ,7406 .4COO 2.1539 4 . 7 6 Q 6 . 5 0 0 0 1.9154 .5303 - 7 7 9 9 - 6 0 0 0 1.6841 .6000 .I3123 . 7 0 0 0 1.4889 .7000 - 8 3 4 5 . 8 0 0 0 1.2721 .en00 . R ~ O I .9000 1.1058 . 9 r 0 0 - 8 7 5 4 1.0000 1.1976 1.0700 1.1976 ALPHA = 12.270 D E G DYNAYIC P R E S S U R E = 8.656 L R F / S Q . F T . F L ~ P = * OE'; W I N G U P P E R S U R F A C E W I Y G L O W E R S I J R F A C E X / C C'P X / C C ' P

TABLE 11. - CONPINUED

P R E S S I l R E O I S T R I R U T I O N ON 4415 W I N G A L P H A = 1 3 . 2 ~ O E G ~ Y N ~ Y I C P R F S S U R E = 8 . 7 1 1 LRFISQ.FT. F L A P = n DEG ' d l N G TIPPER SURFACE W I N G LOWER S U R F A C E F L A P = 0 DEG A c P P 9 = 1 4 . 3 P n 0 E G D Y N 4 M I C P R E S S U R E = 8 . 7 2 1 L B F / S Q . F T .

W I N G LOWER S U R F A C E W I N G I J P P k I I SURFACE A L P H A = 15.35q D C G OYNAY I C P R E S S U R E = 8 . 6 5 7 L B F / S Q . F T . F L A P = O DEG U 1 Y G TIPPER SURFACE W I N G LOWER C U R F A C E

TABLE 11. - CONTINUED

PRESSURE D I S T R I B U T I O N ON 4415 WING ALPHA = 1 6 . 3 8 0 DEG DYNAMIC PRESSURE = 8.745 LBF I S Q - F T . F L A P = 0 G E G WING UPPER SURFACE W I N G LOWER SURFACE ALPHA = 17.360 D E G DYNAMIC PRESSURE = 9.059 L B F / S O . F T . F L A P = 9 D E G WING UPPER SURFACE WING LOWER SURFACE ALPHA = 18.360 DEG DYNAMIC PRESSURE = 8.684 L R F / S Q . F T . F L A P = 0 1 E ; WING UPPER SURFACE WING LOWER SlJRFAfE

X / C CP

X / C cb

0.3Q00 1.2592 .005o 1.4n51 .OlO" ,6663 ."I75 .I571 .MOO -029" .Q750 .I159 1 .239" . 7 0 C O .5n62 - 3 9 0 9 .6276 .4000 .7199 .5nrq .7hhi .6003 .HZ94 .730'l .R773 . B n 0 5 . 9 6 1 1 .9nnr 1.0727 1 . 0 " " " 1.7395

TABLE 11. - COITCLUDED

P R E S S U R E D I S T R I B U T I O N O N 4 4 1 5 W I N G 4 i P l l 4 = 1.9.340 DEG D Y N A M I C PRESSURE = 8.611 L R F / S Q . F T . F L A P = 0 DEG W I N G !JPPER S I J R F A C E W I N G L O W E R S I I R F A C E o. o n o o

. 0C50

. 0 1 0 0 . 0 1 7 5 . 0 5 0 0 . 0 7 5 0 .1r'-lo . 2 " 0 0

. -3r'oo

.4Cl'J0 .501)r) . 6 0 p 0 .7ni)o .80i)O . 9 0 0 9 I . w o o n L D i i 4 = 23,340 D E G D Y V A Y I C PRESSURE = 8.757 L R F / S Q . F T , F L A P = 0 OEG WIhG U P P F P S U R F A C F W I N G L O W E R S U R F A C E PRESSURE D I S T R I B U T I O N ON 4 4 1 5 WING

ALPHA = - 5 . 0 1 0 OEG DYNAYIC PRFSSURE = 2 1 . 2 3 8 LRF/SQ.FT. FLAP = " I j E C

WING UPPER SURFACE WING LOWER SURFACE ALPHA = - 4 . 0 7 ~ O E G DYNAYIC P R E S S U R E = 2 1 . 3 8 4 L R F / S Q . F T . F L A P = n ~ E C , WING UPPER SURFACF WING LOWER SURFACE ALPHA = -2.990 OEG DYNAMIC PRESSUSF = 2 1 . 4 6 6 LRF/SQ.FT. F L A P = n D F G WING UPPER SURFACE WING LOWER SllRCACE Note: The conversion f a c t o r from pounds force/sguare foot t o newtonsjsquare meter is 47.813025e

TABLE 111. - CO1UTINUED

PRESSURE O I S T R I B U T I O N O N 4 4 1 5 W I N G A L P H A = -1.999 D E G O Y N A Y I C P R E S S U R E = 21.393 L R F / S Q . F T . F L A P = 0 OEG W I N G ( I P P F Q SIJRFACE W I N G LOWER S U R F A C E ALPHA = -.983 D E G DYNAY I C P R E S S U R E = 21.466 L R F / S Q . F T . F L A P = 0 DEG W I N G U P P E R S U R F A C F W I N G LOWER S U R F A C E ALOHA = .Chn U F G D Y N A M I C P R E S S U R F = 21.393 L R F / S Q . F T . F L A P = D OEG W I N G l l P P F R SlJRFACF W I N G LOWER S U R F A C E

X / C cb X / C C ' P

c.OCP3 . I 7 0 0 0.0l'oo . l o o n .Q05" ."676 - 0 0 5 0 - 6 4 3 9 . 0 l n 0 . 3 h l b . D l O C 1 . 0 2 9 0 . 0 1 7 5 - 5 5 5 7 - 0 1 7 5 1.3877 .0510 i.3n24 .05Of? 1 . 6 2 7 9 . n 7 5 0 1 . 4 n ~ 3 .0750 1.5817 . I C 0 @ 1.60Q7 . i ? ~ n 1.5641 .ZOO0 1.R434 .men i . z q 8 a . 3 c n o 1 . ~ ~ 4 .30DC 1.1912 . 4 c n 0 1.7346 .40nC 1.1266 . 5 0 1 3 1.6376 - 5 0 0 0 l . n S 6 5 . 6 i ' Q T 1.5494 . 6 0 ? 0 1.0193 . 7 " n o 1.4142 -7OC" - 9 7 4 6 . ~ n n n i . z t j i 3 .anon . 9 3 7 ~ .9"-O 1.p319 . ~ n n - 8 9 6 7 i . n ? r r . ~ 6 7 3 i . n n o o .ti673 PRESSURE O l S T R I B U T I O N ON 4 4 1 5 WING ALPHA = 1.070 OEG DYNAMIC PRESSORE = 2 1 . 3 5 7 LSF/SQ.FT. FLAP = fl DiG WING UPPER SURFACE WING LOWER SURFACF ALPHA = 2.110 DEG DYNAMIC PRESSURE = 2 1 . 4 1 1 LBF/SQ.FT.

F L A P = ? DEG WING UPPER SURFACE WING LOWER SURFACE X I C C ' P X I C C'P ALPHA = 3.130 OEG DYNAMIC PRESSURF = 21.430 L?F/SQ.FT. FLAP = C O E T , WING UPPER SURFACE WING LOWER SURFACE

TABLE 111. - CONTlX.JFD

PRFSSUQE DISTRIRUTION ON 4 4 1 5 WING A L P i H A = 4 . 1 7 0 DFG DYNAMIC PRESSURE = 21.457 LRF/SQ.FT.

FLAP = 0 OEG WING IIPPER SlJRFACE WING LOWER SURFACE X/C C'P

X/C CP

f'.OOOQ . 0 7 Q l . 0 0 5 0 . 7 6 2 1 . O l n n 1.1373 - 0 1 7 5 1.4334 . 0 5 q 0 2.1369 . 0 7 5 0 2.1721 .1"00 2.2190 . 2 0 0 0 2.0812 - 3 0 0 0 2.0460 . 4 0 0 0 1.9141 . 5 0 0 9 1.7236 . 6 0 0 0 1.5975 . 7 0 0 0 1.4715 ROC^ 1.2839 .sono i . n w 4 1.0000 .8559 P L P H P = 5.210 DEG DYNAMIC PRESSURE = 21.329 LRFISQ-FT.

FLAP = I3 DEG WING UPPER SURFACE WING LOWER SURFACE A P P i i A = 6.763 DEG DYY4MIC PRFSSIJRE = 21.756 LRF/SQ.FT. FLAP = 0 OEG WING llPPER SURFACE WING LOWER SURFACE

TABLE 111. - CONTINUED

PRESSURE D I S T R I B U T I O N ON 4415 WING

ALPHA = 7.300 DEG DYNAMIC PRESSURE = 21.138 LRF/SQ.FT. F L A P = " 9 E G

WING UPPER SURFACE WING LOWER SURFACF X / t C'P x / c C ' P 0.0000 .5594 .0050 1.8686 .0100 2.2048 -0175 2.2792 .0500 2.6839 -0750 2.5738 .lo00 2.6244 -2000 2.4578 .3000 2.3239 ,4000 2.0055 .SO00 1.8151 .6000 1.6365 -7000 1.4758 -8000 1.2735 -9000 1.0265 1.0000 .a569 ALPHA = 8.313 OEG DYNAMIC PRESSURE = 2 1 . 4 3 9 LRF/SQ.FT.

F L A P = c D E G WING UPPER SURFACE WING LOWER SURF4CE RLPHA = 9.380 OEG DYNAMIC PRESSURE = 21.512 LRF/SQ.FT.

F L A P = 0 O F G WING UPPER SURFACE WING LOWER SlJRFACE I

X / C cb

X/C c P

TABLE 111. - CONTINUED

PRESSURE D I S T R I B U T I O N ON 4 4 1 5 WING A L P H A = 1 0 . 4 0 0 OEG DYNAMIC PRESSURE = 2 1 . 3 1 1 LRF/SQ.FT. FLAP = 0 OEG WING UPPER 5URFACE WING LOWER SURFACE A L D H 4 = 1 1 . 4 6 0 Q € G DYNhMIC PRESSURE = 21.Q55 L R F I S Q - F T . F L A P = 0 OEG WING UPPER SIJRFACE WING LOWER SURFACE A L Y H A = 1 ? . 5 r p DEG OYNAYIC PRESSIJRE = 21.220 LBF/SQ.FT. F L A P = O DEG N I N G UPPER SURFACF WING LOWER SURFACF

X/C cb

x / c cb

TABLE 111. - CQWmNLTED

PRESSURE D I S T R I B U T I O N ON 4 4 1 5 W I N G a L P H A = 13-500 O E G D Y N A M I C P R E S S U R E = 21.147 L 8 F I S Q . F T . F L A P = ? D E G W I N G U P P E R S U R F A C E W I N G LOWER S U R F A C E X / C cb X / C C'P lEPWA = 14.520 D E G D Y N A M I C P R E S S U R E = 21.010 L B F / S Q . F T . F L A P = 0 D F G W I N G U P P E R S U R F A C E W I N G LOWER S U R F A C E I X / C C'P X / C C P ALPHA = 15.550 O E G DYNAMIC P R E S S U R E = 20.973 L B F / S Q . F T .

F L A P = 0 DtG W I N G U P P E R S U R F A C E W I N G LOWER T U R F A C E

X / C cb

O.OnCO 2.6270 - 0 0 5 0 1 ~ 0 1 6 6 .0100 . 4 1 6 8 . @ 1 7 5 . 1 0 s n .r)500 . 0 9 0 n - 0 7 5 3 .18Rq - 1 3 0 0 . 3 1 7 9 .20Cn . 5 2 2 5 - 3 0 0 0 * 6 3 3 7 .4300 - 7 0 7 4 . 5 C 3 .7595 a6000 . 8 1 7 q - 7 0 3 0 - 8 4 7 5 .9(?n0 - 9 1 0 6 - 9 9 0 0 - 9 7 6 4 1.0703 1.2415

TABLE 1 1 1 . - CONTIIWED

PRESSURE D I S T R I B U T I O N ON 4 4 1 5 WING F L A P = 0 OEG ALPHA = 1 6 - 5 8 ' P F G D Y N A M I C P R E S S U R E = 21.138 LHF/SQ.FT.

W I N G LOWER S U R F A C E W I N G U P P E R SURFACE

X / C cb

o.cono 2.7642 .On50 4.4543 .O100 4.5317 . 0 1 7 5 4.5882 .05Cn 4.1627 .n750 3.6152 - 1 0 0 0 3.2909 . 2 ? 9 0 2.4340 . 3 0 0 0 1.6276 . 4 0 0 0 1 . 3 9 8 5 . 5 0 0 0 1.4699 .6On0 1.4461 .7Pn9 1.4074 .BP00 1.4729 . 9 0 0 0 1.4758 1.0000 1.7884 A L P Y A = 17.580 D E G O Y N A Y I C P R E S S U R E = 21.019 LRF/SQ.FT. F L A P = D DEG W I N G U P P F R SURFACE W I N G LOWER S U R F A C E ALPHA = 1 8 . 5 8 0 D E 6 D Y N A M I C P R E S S U R E = 21.046 L B F / S Q . F T . F L A P = 0 DEG W I N G I l P P F R SIJRFACE W I N G LOWER S U R F A C E

TABLF 111. - CONCLUDED

PRESSUPE D I S T R I B U T I O N ON 4 4 1 5 WING A L P H A = 19.580 D E G OYNAY l C P R E S S U R E = 20.782 L R F / S Q . F T . F L A P = 7 D t S W I N G U P P E R SURFACE W I N G LOWER SURFACE A L P H A = 20,590 D E G DYYANIIC P R E S 5 t J R E = 2 0 . R h 4 L R F / S Q . F T .

F L A P = 7 I ) k L W I N G lJPPER S U R F A C F W I N G LOWER S U R F A C E

X / C cb

TABLE I v PRESSURE DISTRIHUTION ON 4 4 1 5 WING A L P H A = -5.110 DEG DYN4WlC PKFSSURE = 59.368 LaF/SO.FT. FLAP = O OEG WIYG IJPPGK SURFACE WING LOWFR SlJRFACE

X /C cb X / C cb

n . 7 n n ~ . 7 ? u s 0.OOCO . 7 2 8 9 . T ~ C . n 1 4 8 . O M 0 2 . 7 4 6 6 . 3 1 0 1 . 0 1 ? 1 - 0 1 0 0 3.0967 - 0 1 7 5 .0551 . D l 7 5 3.2207 .050C .5901 - 0 5 0 0 2.7717 - 0 7 5 0 - 8 2 5 7 - 0 7 5 9 2 . 4 7 9 1 . i ~ c n 1 . 0 1 1 ~ . I 0 0 9 2.2852 - 2 0 - n 1.3465 .2OC'l 1.6044 .?'I00 1.4991 .3000 1 . 4 0 4 9 . 4 9 0 1 1.4996 - 4 7 0 0 1.3091 . ~ n o 1.4535 . s o n o 1 . l a 4 5 .bOPC 1.7953 .6000 1.1160 . 7 n n 0 1.3465 - 7 0 9 0 1 . 0 4 4 9 .90"3 1.1072 .Rr)nn . 9 8 3 9 . W C O l . n n ~ 2 . w o n . 9 1 6 9 i . ? n n o .u645 i . o o n n .a645 A L P H A = -4.949 nEG DYNAYIC PRF5SURE = 59.386 LSF/SQ.FT. FLAP = 0 DEG WINS IJPPEY SUQFACF WING LOWER SURFACE

X / C cb X/C cb

o . n c ? o . h i 4 3 O.OO0~ - 6 1 4 3 - 7 0 5 0 .on11 . n o 5 0 2.1712 . o i o n 7.5005 . 0 1 : 3 ."378 . " I 7 5 - 1 5 4 6 .0175 7.9083 .05117 .784A .0500 2.5143 . " 7 5 n . 9 7 n 1 .0750 2.1987 . i ~ q r 1.1512 .1300 2.Q504 -2'300 1.5467 . ? r n ~ 1.4475 .300n 1 . 3 6 6 7 .3""0 1.6505 . 4 n r o 1.5762 - 4 0 0 0 1.2399 - 5 " r ' l 1.4538 - 5 7 0 0 1 . I 3 6 6 . f i n o n 1 . 4 1 2 ~ .beno 1.0764 .7C90 1.3493 . 7 n n ~ 1.0704 .8009 . 9 7 2 6 .87On 1.7084 - 9 1 7 0 1.0q72 - 9 0 0 0 . 9 1 0 1 1.03C" .R55R 1.0000 - 8 5 5 8 ALP^^ = -3.~170 D E G DYN4Y I C PRESTURF = 59.774 LRF/SQ.FT. FLAP = 0 DEG WING LJPPFR SURFACE WING LOWER CURFACE Note: The conversion factor from pounds force/square foot to newtons/square meter is 47.880258.

l'mm IV. - CONTIMIED

PRESSURE D I S T R I B U T I O N ON 4 4 1 5 W I N G A L P H A = -1.940 D E G D Y N A M I C PRESSIJRE = 5 9 . 3 3 2 L B F / S Q . F T . F L A P = i ?FG W I N G U P P E R SURFACE W I N G LOWER S U R F A C E X / C C ' P X / C c'P A L P H A = -.900 D E G D Y N A M I C P R F S S U K E = 59.892 L B F / S Q . F T . F L A P = n D F G W I N G U P P E R SURFACE W I N G LOWER SIJRFACE A L P H A = - 1 6 0 D E G DYNAMIC P R E S S U R E = 5 9 . 3 4 1 C I F / S Q . F T . F L A P = C DFG W I N G U P P E R S U R F A C F W I N G LOWER S U R F A C F

TABLE IV. - COlQINUED

P R E S S U K F D I S T R I R I J T I O V O N 4 4 1 5 W I N G A:Pql\ = 1,75C1 7 E G D Y N A Y I t P Q F S S U 9 F = 59.648 L B F / S Q . F T . F L A P = B DEG W I N G l J P P E R S I J R F A C E W l N G LOWER S U R F A C E

Y / C cb

X / C cb

~ . O ? O C .on95 0.0OPq .0095 . o e q n - 2 7 3 5 ,005C - 4 4 3 9 * 0 1 " 0 .57c9 . 0 1 3 n .be43 . I l l 7 5 .P56? .0175 1.0766 .C500 1.6133 .0500 1 . 4 4 9 9 - 0 7 5 9 1.64R1 ,0750 1.3961 elnaOO 1.7219 . I 3 0 0 1.4277 . z n n o 1.9723 .2000 1.1675 .3C90 1.9273 -3COO 1 . 1 1 4 5 . 4 q n 0 1.7736 .4300 1.0759 . 5 9 n 0 1.5565 - 5 0 0 0 - 9 9 5 7 . m q o 1.5477 - 6 0 0 0 .9R05 . 7 n ~ o 1.4381 ,7000 - 9 4 3 5 .8@'30 1.2622 .ROO0 .929P . q P n n 1.7302 . 9 0 @ 0 - 8 8 6 7 l Q C G q n .8hP9 1.0Q00 - 8 6 8 9 4 k P H 4 = 7.34" 9 E G D Y N A Y I C P K F S S U R F = 59.287 L R F / S Q . F r . F L A P = 0 D E G W I N G U P P F R S U R F A C E W I N G L O W E R S U R F A C E ALPH4 = 3 . 4 3 7 D E G D Y N A M I C P R E S S U K F - 59.133 L R F / S O . F T .

F L A P = 0 D E G f . I l Y ? i l P P E F S I J R F A C E K I N G LOWER S U R F A C F

TABLE IV. - C O I v n N U m

P R F S S U R E D I S T R I B U T I O N !IN 4 4 1 5 W I N 6 A L P H A = 4 . 5 1 0 D E G D Y ' V 4 M I C P R E S S l l R E = 5 9 . 3 3 2 L R F / S Q . F T . F L A P = n ritii W I N G U P P E R S U R F A C E W I N 6 L O W E R S l J R F A C F A L P H A = 5 . 5 9 0 D E G D Y N A M I C P R E S S U R E = 5 9 . 5 4 0 L - F / S O . F T .

F L 4 P = ?t< W I N G U P P E Q S U R F A C E W I N G L O W E R S I J R F A C F A L P H 4 = 6 - 7 1 ! ) O E G D Y N P Y I C P R E S S U R F = 5 9 . 7 9 6 L Y F / $ ? . F T .

F L A P = ' rite, W I N G I J P P F R SIJRF A C E

TABLE IV. - CONTI-

P R C 5 S I J P E f ) I S T R I H I I T I U N O N 4 4 1 5 W I N G 4 L P ' i A = 7.7hq ? F G n Y Y / Y I C P R F 5 S U R F = 5 9 . " 1 6 L 8 F I S O - F T . F L A P = O D E G W I N G L O W E R S U R F A C F

X I C cb

d 1 h 5 IJPPFR S I J K t A C t w I Y G L O W E R S l l R F A C E

X I C cb X l C c b

d 1 N G I l P P F P S I I R F A C G W I N G L O W F R S U R F A C F

TABLE IV. - CONTINUED

P R E S S U R E O I S T R I R U T I O N O Y 4 4 1 5 W I N G ALPHA = 19,953 D E F DYNAMIC P R F S S U R E = 59.115 L R F / ~ O . F T . F L A P = r ntr, W I N G L I P P E R S U R F A C E k I N G L O W E R S U R F A C E A L P H A = 12,300 D E G D Y N A M I C P R E S S U R F = 59.142 L R F / S O . F T . F L A P = C n E G M I N G U P P E R S U R F A C E W I N G L O W E R S U R F A C E F L A P = c n E G ALPHA = 1 3 , 0 7 0 D E G D Y N A M I C P R E S S U R E = 59.106 L F l F / S Q . F T .

M B N G U P P E R S U R F A C E W I N G L O W E R S U R F A C E

x / c cb

x / c cb

0,0000 1.9207 0.000C 1.9207 -0050 .5438 -0050 3.5723 .0100 3.8809 .0100 . I 9 1 5 , 0 1 7 5 3.9096 .0175 .0074 , 0 5 0 9 3.9415 .05CO . I 9 6 9 - 0 7 5 0 . 3.465R .0750 .3639 ,1000 3.2881 .I000 .4437 .ZOO0 2.7305 .200n -6041- ,3000 2.3972 .1"00 .69R5 .4000 1.8963 .4000 .7547 ,5000 1.6004 .5noe -7828 -6000 1.3227 .6001 .8232 - 7 0 0 0 1.2684 .7000 .R579 .8000 1.2312 .ROO0 .9227 ,9000 1.2503 .9000 .9735 1.00nn i . I R ? ~ 1.0000 1.1833

TABLE IV. - CONTINUED

PPtSSURE O I S T ~ I B U T I O ~ ON 4 + 1 5 WING ALPM4 = 1 4 . 1 4 7 P F G Q Y Y h Y I C PRESSIJRE = 5 9 . 1 7 8 L'IF/SO.FT.

F L A 3 = ~ 3 t , WING LOWER SlJRFOCf

X/C c'b

4LPHA = 1 5 . 1 2 Q DEC DYN4MIC PRFSSIJRF: = 58.727 LBF/SQ.Fy.

C L 9 P = O C E G WINS VPPFR SURFACE W I N G LOWER S U R F A C E X/C C'P

x / c cb

4 L W A = 1 6 . 1 2 9 O F 6 DYN4MIC PRFSSIJRE = 5 7 . 8 1 5 LRF/SQ.FT.

F L A P - C 3 F G

WING !fPPFR SURFACE X / C I CP

TABLE I V . - CONTINLTED

PRrSCu<E U I S T Q I B I J T I O V I N 441'. W ~ N C ALPHA = 1 7 . 1 5 - n F G n Y N 4 Y I C PRESSIJPF = 5 9 . 6 9 4 L ~ F / ~ I J . F T .

F L n D = - r t , WING UPPER SUQFACF

X / C cb

r . o C r o 2.3817 .'3050 4 . r 5 1 0 - 0 1 G C 4 . " q 7 5 - 7 1 7 5 4 . 1 7 2 1 . 0 5 0 o 4.C951 - 0 7 5 C 2.7536

con 7 . 7 9 2 6

. z o n n 7.c77n .30OC 1 . 4 7 5 3 - 4 C 9 0 1,4764 . 5 0 0 0 1.5344 . 6 0 n @ 1,5733 e 7 0 0 0 1 . 5 6 1 9 .8'700 1 . 5 3 5 4 ~ 9 C n 0 1.55"2 1.00'70 1 . 4 7 2 7 PLPHA = 1 8 . 1 5 0 DEG OYNAYIC PKFSSUNk = 59.773 L q F / S O . T T . F L h V = " O t # I R G UPPEP SURFACE k l N G LIWER ZURFbCF

X / C C'P

X / C cb ALPHA = 1 9 . 1 7 0 DEG DYQPYIC PRESSlJRF = 6 0 . 4 2 4 LRF/SQ.FT. FLAP = OF; WING UPPER SURFACF WINS LOWER SURFACE X / C C'P

X / C cb

0 . OCCO . 0 @ 5 0 .OlOr' - 0 1 7 5 .05r)O

. f'7 5 0

. l o o n . z o o 0 - 3 0 0 0 . 4 0 7 0 . 5 0 n 0 . 6 0 7 0 . 7 o o n . 8 0 0 0 . 9 0 0 0

I. m o o

TABLE IV. - CONCLUDED

P S F S 5 I J R E 9 I S T R I S U T I J U U N 4 4 1 5 W I N G ACP'ICI = 91.147 O t G D Y Y 4 Y I C P Z E S S U K F = 5 9 . 9 2 3 L R F / S Q . F T . F L A P = O D F G A I N G C P P F K S I J R F A C F W I N G L O W E R < I I R F A C C A L P r l 3 = ?I.>?' L,FS O Y ~ J A Y I C P R F S S U I ~ F = 5 9 . 2 7 9 LIF/SQ.FT.

F L A P = ' 3 O E G W I N G C O W E R C I J K F A C E X / C C ' P PRESSURE O I S T R I B U T I O N ON 4 4 1 5 W L N G ALPHA = - 0 7 0 OEG DYNAMIC PRESSURE = 4 . 5 3 5 L R F / S Q . F T . F L A P = 4C ?ti WING UPPER SURFACE WING LOWER SURFACE F L A P UPPER S U R F 4 C F F L A P LclviFR S I J d C A C F ALPHA = .190 OEG DYNAMIC PRESSURE = 9.861 LRF/SQ.FT. F L A P = 40 D E b M I N G UPPER SURFACE M I N G LOWER SURFACE F L A P UPPER SURFACE F L A P LOWFR SURFACE A L P H A = . 3 8 0 0 E G DYNAMIC PRESSURE = 15.620 LBF/SQ.FT. F L A P = 40 D E G WING UPPER S U R F A C E WING LOWER SURFACE F L A P UPPER SURFACE F L A P LOWER S U R F A C E

x / c C ' P x I C c'P X I C C ' P X / C cb

0.0000 ,4832 .0050 1.5539 .Dl00 2.1511 ,0175 2.4266 ,0503 2.9194 ,0750 2.7909 .1000 2.8875 .ZOO0 2.7638 -3000 2.6739 ,4000 2.4710 .5000 2.4121 ,6000 2.2613 .7000 2.2130 .8003 2.1231 .9000 1.9733 1.0000 2.4555 Note: The conversion factor from pounds force/square foot to newtons/square meter is 47. ,380258.

TABLE V . - CONTINLTED

P R F S S U R E O I S T R I B U T I O N O N 4 4 1 5 W I N G F L A P = 4 0 D E G O Y N A N I C P R E S S U R E = 2 1 . 3 8 4 L R F / S Q . F T . 4LPYW = ,540 O E G W I N G J P P E R S U R F A C E W I N G LOWER S U R F A C E F L A P U P P E R S U R F A C E F L A P COWER S U R F A C E

X / C cb

X /C c ~ P x /c C ' P x / c cb

0 , 0 0 0 0 - 6 7 7 7 - 0 0 5 0 1 , 7 1 6 7 .0100 2.7659 - 0 1 7 5 2 . 4 6 0 0 .0500 3.1073 .0150 2 , 9 8 7 3 . I 0 0 0 2.8551 - 2 0 0 0 2 . 7 2 1 9 . 3 0 0 W 2 . 6 6 2 6 - 4 0 0 0 2.5115 ,5000 2.4014 ,6000 2.2504 - 9 0 0 3 2 , 2 2 2 1 .8000 2.1247 ,9000 1.9871 1,00433 2 , 4 4 9 4 i L A P = 4 0 OEG M L P h h = - 7 9 0 D E G D Y N A M I C P R E S S U R E = 31.273 L B F / S Q . F T .

WING LOWER S U R F A C E F L A P U P P E R S U R F A C E F L A P L O U E R S U R F A C E k I N G 3 P F W S U R F A C E

X I C cb

TABLE V. - CONCLUDED

PRESSURE D I S T R I B U T I O N ON 4 4 1 5 WING DYNAMIC PRESSURE = 4 1 . 4 6 2 LRF/SQ.FT. ALPHA = 1 . 0 3 0 OEG F L A P = 40 I-iEC, M I N G UPPER SURFACE WING LOMER SURFACE F L A P UPPER SURFACF ALPHA * 1.240 OEG OYNAN l C PRESSURE = 4 8 . 4 6 1 LBF/SQ.FT.

F L A P L O M E R S U R F A C E M I N C UPPER SURFACE WING LOWER SURFACE F L A P UPPER SURFACE

x / C cb

TABLE V I PRESSURE OISTRIBUTION ON 4 4 1 5 WING B L P M A = -4.800 DEG DYNAMIC PRESSURE = 8.840 LBF/SQ.FT.

FLAP = 4 0 DEG M W G UPFEa SURFACE WING LOWER SURFACE FLAP UPPER SURFACE FLAP LOWER SURFACE X I C C ' P X/C C ' P X/C c'P X/C c'P A L P H A = -3.860 DEG DYNAMIC PRESSURE = 8.931 LBF/SQ.FT. FLAP = 4 0 OEG FLAP LOWER SURFACE W I N G UPF'Ei4 SURFACE WING LOWER SURFACE FLAP UPPER SURFACE

X BlC C ' P x /C cb X / C c'P X/C C'P

0,0030 - 0 2 2 0 .0053 .4667 .OLUCI - 7 7 7 9 - 0 LOO ,0175 1,1380 .050Cl 2.0326 .075C! 2.1222 ,1000 2.1662 ,2003 2.2507 .300Cl 2.3403 .400C! 2.2473 .5000 2.1898 ,6000 2.1205 .700C! 2.1036 ,8000 2.0630 ,9003 1.9785 B.OOOC! 2.4063 DYNAMIC PRESSURE = 8.968 LBF/SQ.FT. ALPHA = -2,850 OEG FLAP = 4 0 OEG H I N G UPlPER SURFACE WING LOWER SURFACE FLAP UPPER SURFACE FLAP LOWER SURFACE

X IC cb X / c C'P x ; c 1P

x / c C'P 0,00013 - 0 2 8 6 0.0000 - 0 2 8 6 .00513 . 5 7 2 6 .0050 - 0 2 6 9 .Ok013 .9313 - 0 1 0 0 - 1 6 6 7 .0175 1.2344 - 0 1 7 5 .3536 - 0 5 0 3 2.1353 - 0 5 0 0 .7679 ,8750 2.2010 - 0 7 5 0 ,8521 -10013 2.1774 . l o 0 0 .9009 - 2 0 0 3 2.3745 .ZOO0 .a677 - 3 0 0 3 2.3745 - 3 0 0 0 .8182 - 4 0 0 3 2.3223 .4000 .7686 ,50013 2.2482 ,5000 - 6 7 1 3 .Q000 2.1909 - 6 0 0 0 .5910 - 7 0 0 3 2.1572 .7000 . 5 2 4 4 ,8000 2.0932 .8000 .4663 - 9 6 0 3 1.9703 - 9 0 0 0 - 3 7 0 6 1,3003 2.4452 1.0000 2.4452 Note: The conversion factor from pounds force/square foot to newtons/square meter is 47.880258.

TABLE VI. - CONTINUED

PRESSURE D I S T R I B U T I O N O N 4 4 1 5 W I N G ALPHA = -1.830 OEG D Y N 4 Y I C PRESSURE = 8.913 L R F I S Q - F T .

M I N G UPPER SURFACE W I N G LOWER SURFACE F L A P UPPER SURFACE ALPHA = - . 8 5 0 DEG D V N 4 H I C PRESSURE = 8.994 L B F / S Q . F T .

U I N G UPPER SURFACE WING LOWER SURFACE F L A P UPPER SURFACE F L A P COWER S U R F 4 C "

x t c cb

OYNAMIC PRESSURE = 8.895 L B F / S Q . F T . F L A P = 4.0 DFG M E N 6 UPPER SURFACE WING LOWER SURFACE F L A P UPPER SURFACF F L 4 P COWER SURFLICE X /C C(P

TABLE V I . - CONTIN'&%

PRFSSURE OISTRIRIJTION ON 4 4 1 5 WING OYNAY IC PRESSURE = 8.895 LRF/SQ.FT. ALPi-l.4 = 1,150 OEG FLAP = 4 C OEG W i N G dF1PER SURFACE WING LOWER SURFACE FLAP UPPER SURFACE FLAP LOWER SURFACE .loor, - 2 0 0 0 .3000 .4000 .5000 .6000 .7000 - 8 oon .9 000 1 .0000 A L P h & = 2.170 OEG DYNAMIC PRESSURE = 8.840 LRF/SQ.FT. FLAP = 4 0 DEG 4.I:RIG U P f ' t E SURFACE WING LOWER SURFACE FLAP UPPER SURFACE FLAP LOWER SURFACE A L P H A = 3.180 OEG DYNAMIC PRESSURE = 8.830 LRF/SQ,FT. FLAP = 4 0 OEG b d JNC LIPPER SURFACE WING LOWER SURFACE FLAP UPPER SURFACE FLAP LOWER SURFACE

TABLE VI. - C O r n I W E D

PRESSURE D I S T R I B U T I O N ON 4 4 1 5 W I N G A L P H A = 4.210 O E G O Y N A M I C PRESSIJRE = 8 , 8 8 5 L R F / S Q . F T . F L A P = 40 O E G W I N G U P P E R S U R F A C E W I N G LOWER S U R F A C E F L A P UPPER S U R F A C F x / t c'p X / C C ' P A L P H A = 5.220 OEG D Y N A M I C P R E S S U R E = 8 . 8 0 3 L B F / S Q . F T , WING U P P E R S U R F A C E MBMG LOWER S U R F A C E F L A P UPPER S U R F A C E F C A P LOWE9 S U R F 4 C C

X / C IP

X l C C ' P X / t C ' P ALPHh = 6 . 2 6 0 OEG D Y N A N l C P R E S S U R E = 8.977 L B F / S Q . F T . F C A P = 40 DTG W I N G UPPER S U R F A C E W I N G LOWER S U R F A C E F L A P U P P E R S U R F A C E F L A P LOWER S U R F w t E

X/C cb X / C C'P

TABLE VI. - CONTINUED

PRESSU&E DISTRIBUTION ON 4 4 1 5 WING A L P H A = 7.270 DEG OYNAMIC PRESSURE = 8.895 LBFISQ-FT, FLAP = 4 0 OEG w i V G UPPILR SURFACE WING LOdER SURFACE FLAP UPPER SURFACE FLAP LOWER SURFACE XIC C ' P A L P H A = 8.280 OEG DYNAN I C PRESSURE = 8.940 LBF/SQ.FT. FLAP = 4 0 OEG FLAP LOWER SURFACF H S N G UPPER SURFACE WING LOWER SURFACE FLAP UPPER SURFACE

x / c Cb X / C C ' P x / c IP x / c C ' P

0.0000 3.6894 0,0003 3.6894 .005Cl 5.4564 - 0 0 5 0 1.7062 .OBOO 5.8618 - 0 1 0 0 - 7 9 9 0 -0175 5,6270 .0175 - 2 5 8 5 .0500 5.1371 .@SOD .0236 .0750 .0946 .0740 4.6236 , Y 003 4.3009 - 1 0 0 0 . I 5 3 7 .ZOO0 3.5830 .ZOO0 . 3 5 8 1 .3000 3.2654 .3000 .4095 ,4000 2.8633 .4000 .4215 .5003 2.5829 .5000 - 4 2 3 2 $ 6 0 0 0 .4129 .bC00 2.4106 .TO03 2.2366 .7000 .3718 .8000 2.0660 .8000 - 3 5 8 1 .90O0 1.8633 - 9 0 0 0 . 2 8 1 0 1,0000 2.0728 1.0000 2.0728 ACPHW = 9.330 OEG DYNAMIC PRESSURE = 8.940 LRF/SQ.FT.

FLAP = 4 0 OEG W I N G U P P E X SURFACE WING LOWER SURFACE FLAP UPPER SURFACE FLAP LOWER SURFACE

x i c C ' P X / C CP X/C c'p

X /C C ' P 0,0000 4.6219 0.0000 4.6219 -0050 6.0291 - 0 0 5 0 2.1116 .OL00 6.1085 - 0 1 0 0 - 9 6 4 6 .0100 2.4669 -0175 5.8044 . D l 7 5 ,3379 .0503 5.4682 - 0 5 0 0 .0068 ,0500 2.3913 -0750 4,9040 .0750 - 0 5 7 4 ,1000 4,5087 - 1 0 0 0 . I 2 8 4 . l o 0 0 2.2317 .2003 3.6708 .ZOO0 .3016 -3000 3.2772 - 3 0 0 0 ,3752 - 3 0 0 0 1.4804 -4003 2.8819 - 4 0 0 0 ,4044 ,5000 2.6302 .5000 - 4 1 4 6 - 5 0 0 0 1.3759 -6000 2.3599 - 6 0 0 0 - 4 0 0 9 .7003 2.1302 - 7 0 0 0 - 3 8 3 8 .7000 1.3604 ,8000 1.9477 .8000 .3615 ,9000 1.7957 .9000 .2998 - 9 0 0 0 1.3433 1,0003 1,8616 1.0000 1.8616 1.0000 1.2868

TABLE V I . - COllYCNTED

PRESSURE D I S T R I B U T I O N ON 4415 WING O Y N A M I C PRESSURE = 8.940 LRF/SO.FT. F L A P = 4 0 OtG A L P H A = 13.320 OEG M I N G UPPER SURFACE WING LOWER SURFACE F L A P UPPER SURFACE F L A P C O W E F ( U R F A C L X / C C*P

X /C C'P X/C cb

b L P H A = 11.290 OEG D Y N A M I C PRESSURE = 8.895 LBF/SQ.FT. F L A P = 40 D E C MING U P P E i I SURFACE WING LOWER SURFACE F L A P UPPER SURFACE F L A P LOWER S U R F A C t

x / c d p X /C c'p X I C c'P

X l C CP

0-0000 4,9746 0.0003 4.9746 -0050 6.7319 -0050 2.7624 .0100 6.5825 ,0100 1.2853 . 0 ! . 0 0 2.4017 -0175 6.1699 ,0175 -6112 -0500 5.6181 .0500 -0051 .0500 2.2085 -0750 4.9169 -0750 -0475 .1000 4.5077 .I000 .0917 -1000 1.9756 .2000 3,7183 -2000 ,3014 .3000 3.2751 -3000 -3530 .3000 1.4724 .4003 2.7250 -4000 -3944 -5000 2.5128 .5000 -4047 .5000 1.3880 -6000 2.2326 -6000 .3978 .7000 1.9916 .7000 -3720 .7000 1.3604 -8000 1.8727 .8000 .3634 -9000 1.6554 -9000 -3341 -9000 1.3312 leOOOO 1.5620 1.0000 1.5620 1.0000 1.4517 A L P H A = 12.280 DEG DYNAMIC PRESSURE = 8.730 L B F I S O - F T . F L A P = 40 O t G XING LOWER SURFACE F L A P UPPER SURFACE F L A P LOWER SURFACF WING UPPER SURFACE X /C csp

TABLE V I . - CONCLUDED

PRESSURE D I S T R I B U T I O N O N 4 4 1 5 WING BLPI-rA : = 1 3 - 2 4 0 D E G D Y N A M I C PRESSURE = 8.748 L B F / S Q . F T . F L A P = 40 OEG M I N G U P P f K S U R F A C E W I N G COWER S U R F A C E F L A P U P P E R S U R F A C E F L A P LOWER S U R F A C E D V M A N l C P R E S S U R E = 8.757 L B F / S Q . F T . F L A P = 40 DEG M I U G U P P E 4 S U R F A C E W I N G LOWER S U R F A C E FLAP U P P E R S U R F A C E F L A P L O W E R SURFACE

>:IL cb

0,8000 5.6170 -0050 6 , 5 4 8 3 ,0900 6 , 5 3 2 7 . 0 % 7 5 6 , 2 7 4 1 .0505 5 , 5 6 8 7 -0750 4.7806 -1003 4.3184 .2000 3.4112 - 3 0 0 3 2 , 9 5 2 5 .LO00 2 , 6 0 0 7 .SO03 2 , 3 4 2 0 .6000 1.8919 -7000 1 , 6 5 5 6 .8003 1.9867 -9000 1.9505 I,OOGO 2 , 6 0 5 9 PRESSURE D I S T R I B U T I O N ON 4 4 1 5 WING ALPHA = - 4 , 6 1 0 OEG DYNAMIC PRESSURE = 21.402 L R F / s Q . F r . F L A P = 4 r PEG M I N G UPPER SURFACE WING LOWER SURFACE F L A P UPPER SURFACE F L A P LOkIER S i r l i F A C f

X6C c'P X / C C'F

ALPHA = - 3 . 5 8 0 DEG OYNANEC PRESSURE = 2 1 . 3 8 4 L 8 F I S Q . F T . F L A P = 4 r D E G Y I N G UPPER SURFACE WING LOWER SURFACE F L A P UPPER SURFACF F L A P L O W E R S1IRFACF

X I C .sp

X I C C ' P X I C C ' P ALPHA -2.600 DEG OYNAMlC PRESSURE = 2 1 - 3 5 6 L 8 F I S Q . F T . F L A P = 40 OETG Y I N G UPPER SURFACE W I N G LOMER SURFACE F L A P UPPER SURFACE F L A P LOWER S t I R F P C E Note: The conversion factor from pounds forcelsquare foot to newtons/square meter is 47 .i!CuZj8

TABLE VII. - CONT-

PRESSURE O I S T R I 8 U T I O N ON 4 4 1 5 W I N G A L P H A = - 1 . 5 5 3 O E G D Y N A M I C P R E S S U R E = 2 1 . 4 2 0 L B F / S Q . F T .

F L A P = 4 0 UEG WING WPPEd S U R F A C E W I N G LOWER S U R F A C E F L A P U P P E R S U R F A C E F L A P LOWER S U R F A C E

X / C C ' P x / C cb

A L P H A = - . 5 7 3 D E G D Y N A M I C P R E S S U R E = 2 1 . 4 3 9 L B F / S Q . F T . F L A P = 4 0 OEG H I N G V P P E d S U R F A C E W I N G LOWER S U R F A C E F L A P U P P E R S U R F A C E F L A P LOWER S U R F A C E X J C C'P X / C C'P A L P H A = .470 D E G F L A P = 4 0 OEG H I M G UPPER S U R F A C E W I N G LOUER S U R F A C E F L A P U P P E R S U R F A C E F L A P LOWER S U R F A C E

x / c CP X /C C ' P

TABLE TTI. - CONTINUED

PRESSURE D I S T R I B U T I O N UN 4415 WING F L A P = 40 O E G DYNAMIC PRESSURE = 21.393 LRF/SP.FT. ALPHA = 1.500 OEG WING LOWER SURFACE F L A P UPPER SURFACE F L A P L O W E R S U R F A C E d I N G UPPER SURFACE

x / c CP

X/C c'P X /C C ' P X/C C'P 0.0000 1.0794 .0050 2.2703 .0100 2.5809 .0175 2.9367 -0500 3.5227 .0750 3.0624 -1000 2.9805 .2000 2,8428 .3000 2.7948 -4000 2.5739 ,5000 2.4291 -6003 2.3127 .7000 2.2442 -8000 2.1355 -9000 2.0035 1.0000 2.4320 &LPHA = 2.550 OEG DYNAMIC PRESSURE = 21.439 L B F / S P . F T . F L A P = 4 0 D E F M I N G UPPER SURFACE WING LOWER SURFACE F L A P UPPER SURFACE F L A P LOWER S U R F A C E

X /C cb x/c cb x/c cb X / C C$

0.0000 1.2320 0.0000 1.2320 .0050 2.7945 .DO50 .3346 .0100 3.0650 .0100 -0282 .0100 3.3944 ,0175 3.4728 .0175 -.0014 -0503 3.4961 .0500 .2029 .0500 3.2543 - 0 7 5 0 3.2580 .0750 -3564 1000 3.2291 .lo00 -4501 .I000 3.1369 .ZOO0 2.9227 -2000 -5273 -3000 2.8487 .3000 .5394 .3009 2.1447 .4003 2.5775 .4000 .5344 .5COO 2.4331 .5000 ,4994 .5000 1.3150 .6003 2.3331 ,6000 .4916 -7000 2.2492 ,7000 -4480 ,7000 1.1840 -8000 2.1316 .8000 .3601 ,9000 -2987 .9000 1.1754 -9000 2.0104 1.0003 2.4289 1.0000 2.4289 1.0000 1.0910 ALPHA = 3.560 OEG DYNAMIC PRESSURE = 21.356 LBF/SQ.FT. F L A P = 4 0 DEG M I N G U P P E 2 SURFACE WING LOWER SURFACE F L A P UPPER SURFACE F L A P LOWER S U R F A C E

x/c cb

X / C cb

TABLE VII. - CONTINUED

PRESSURE DISTRIBUTION ON 4 4 1 5 WING 4 1 PHQ = 4 . 5 9 0 OEG DYNAMIC PRESSURE = 21.384 LBF/SU.FT. FLAP = 4 0 OEG V R M G U o P E R SURFACE WING LOWER SURFACE FLAP UPPER SURFACE FLAP LOWER SURFACE X /C c'P X/C C ' P X/C C ' P 0 ~ 0 0 0 0 1.7712 .005r) - 4 8 3 1 .0100 - 1 7 8 7 .0175 - 0 4 3 8 .0500 . l o 7 3 .(?750 .22bO . l o 0 0 - 3 1 9 9 - 2 0 0 0 .4835 ,3000 ,4721 ,4000 - 4 8 6 4 - 5 0 0 0 .4678 - 6 0 0 0 - 4 4 3 4 .7000 - 4 1 3 3 .€I000 - 3 3 9 5 ,9000 - 2 7 9 4 P.0000 2.3909 dLP4A = 5 , # 6 5 0 OEG DYNAMIC PRESSURE = 21.457 LBF/SQ.FT. FLAP = 4 0 OEG klNG U P P E R SURFACE WING LOHER SURFACE FLAP UPPER SURFACE FLAP LOUER SURFACE

X / C C S P x / c IP X / C cb X /C c'P

0,0003 2.4036 0.0000 2.4036 .0050 3,8993 - 0 0 5 0 - 9 8 9 6 ,0100 4.1942 - 0 1 0 0 - 4 4 4 8 ,3175 4.5355 .0175 . 0 9 5 7 ,0500 4.7650 - 0 5 0 0 - 0 8 3 1 ,3750 4,0231 - 0 7 5 0 . I 9 6 4 1000 3.8725 . l o 0 0 - 2 7 6 6 ,2030 3.3657 ,2000 - 4 2 6 9 ,3000 3.0603 - 3 0 0 0 .4712 ,4000 2.7872 - 4 0 0 0 .4762 . 5 0 0 3 2.5894 - 5 0 0 0 .4483 ,6000 2.4339 - 6 0 0 0 .4169 . T O 0 3 2.3269 .7000 .4112 ,8000 2,1882 ,8000 ,3427 -9000 2,0313 - 9 0 0 0 .2684 1,3000 2,3677 1.0000 2.3677 FLAP = 40 DEG &IPHA = 6,650 OEG DYNAMIC PRESSURE = 21.530 LBF/SQ.FT.

WING LOWER SURFACE FLAP UPPER SURFACE FLAP LOWER SURFACE ilIMS V P P E ? SURFACE

X / C cb

TABLE VII. - CONTINUED

PRESSURE D [ S T R I B U T I O M ON 4415 MlMG DYNAMIC PRESSURE = 2 1 , 4 9 3 LBF/SQ.FT, F L P P = 46 3E1, ALPHA = 7 , 6 9 0 DEG W I N G eoMER S U R F A C E F L A P UPPER S U R F A C E F L B P L O W E b i b ? F h C F &LPN& = 8,750 DEG DYNAMIC PRESSURE = 2 1 . 4 1 1 LRFISQ.FT. F L A P = ii? REG WING UPPER SURFACE M I N G LOWER SURFACE F L A P UPPER SURFACE F L A P LOWER S I $ ? F A C E X l C C ? P DYNAMIC PRESSURE = 21.439 CBF/SO.FT, F L h P - 4 D r L ALPHA = 9,740 DEG . W I N G UPPER SURFACE W I N G LOMER SURFACE F L A P UPPER SURFACE F L A P LOWER S U R F A C E

TABLE V I I . - CONCLUDED

PRESSURE DISTRIBUTION ON 4 4 1 5 WING d l P M 4 = 13.680 OEG OYNAMIC PRESSURE = 21.439 LRF/SQ.FT. FLAP = 4 0 DEG W I N G UPPER SURFACE WING LOWER SlJRFACE FLAP UPPER SURFACE FLAP LOWER SURFACE

K I C C ' P x I C cb X/C C ' P x / c cb

0,0000 5.1346 0.0000 5.1346 .0050 6.3208 .0050 2.2612 .0 100 .0100 1.1081 -0175 - 0 1 7 5 .5586 - 0 5 0 5 5.5227 - 0 5 0 0 -.DO49 .Q750 4.8542 .0750 .0444 . I 3 0 0 4.5738 . l o 0 0 . I 2 1 9 .PO00 3.6109 - 2 0 0 0 - 2 7 7 9 - 3 0 0 0 3.2249 .3000 - 3 5 7 2 - 4 0 0 0 2.8149 .4000 .3865 - 5 0 0 3 2,5888 - 5 0 0 0 ,3851 ,5000 2.3500 - 6 0 0 0 - 3 9 8 0 - 7 0 0 0 2.2175 .7000 .3680 .8003 1.9463 - 8 0 0 0 .3465 - 9 0 0 0 1.7385 .9000 - 2 5 2 9 1,0003 1.7449 1.0001 1.7449 P t P W d = 11.690 OEG OYNAMIC PRESSURE = 2 1 . 3 6 6 LBF/SQ.Fr. FLAP = 4 0 OEG d I M G V P P E * SURFACE WING LOWER SURFACE FLAP UPPER SURFACE FLAP LOWER SURFACE

X/C cb

R L P M A = 12.730 DEG DYNAMIC PRESSURE = 21.274 LBF/SP.FT.

FLAP = 4 0 DEG M B W G UPPCR SURFACE WING LOWER SURFACE FLAP UPPER SURFACE FLAP LOWER SURFACE

x / c cb

LOCOI~On of Pressure or /,c?s E g Z Z Z T T F i o p s r o T C T p e r ~ e n l chord --- pelcenr chcrc .

Locolion o f pressure orifice Geomefric Choracfer~sf~cs Area, m e f e r 2 / / f " / 0.2477 (267) Chord, cm /I/ 20.32 (8.00) Span, cm ( ~ n ) 12/92 /4800) NACA 4415 Chord, cm 6.096 (240) A ~ r f o i l NACA 4415

1 Center of moments o t .i'5cL >%

-? Q % / -

Figure 1 . - Three-view drawing of model. Dimensions are given in centimeters and

parenthetically in inches unless otherwise noted.

Figure 2.- Sketch shawing setup of model in test section of the Langley 300-MPII 7- by

10-foot tunnel. Dimensions are given in centimeters and parenthetically in inches, I I I I I I I t I/ I I I

0 5 10 15 20 25 30 35 40 45 50 55

q , , /bf/ft2 E g w e 3,- Effect of variation in free-stream dynamic pressure on the longitudinal.

aerodynamic characteristics of the model.

a -- oO.

Figure 4.- Effect of angle of a t t a c k on t h e longitudinal aerody-namtc

characteristics of the model.

o Upper surface

Lower surface

Figure 5 . - Pressure distributions on wing of model at several free-stream

d;ynamic pressures. 6f ~ c : oO.

o Upper surface 0 Lower surface a = - 4 . 9 4 ' to 2 . 0 2 ' .

(a)

Figure 6.- Pressure distributions on wing of model at free-stream dynamic pressure

of approximately 420 ~ / m 2 ( 8 . 8 lbf/f-te). 6f = oO.

o Upper surface Lower surface

3 -

rr=4/Oo a=307"

- c e P O O o o

;7

CP O 0 0 0

o o o n o e e 8

/ I 8 I I a, = 3.07' t o 10.23'.

(b)

Figure 6.- Continued.

0 Upper s u r f a c e

o Lower s u r f a c e

Figure 6.- Continued.

o Upper surface Lower surface a = 17.36' t o 20.34'.

(d)

Figure 6.- Concluded.

0 Upper s u r f o c e o Lower surface a. = - 5 . 0 1 ' to 2 . 1 1 ' .

(a)

Figure 7.- Pressure distributions on wing of model at free-stream dynamic pressme

of approximately 1020 ~ / m 2 (21.3 lbfIft2). 6f = OO.

0 Upper s u r f u c e o Lower surfuce a = 3 - 1 3 ' to 1 0 . 4 0 ' .

(b)

Figure 7 . - Continued.

o Upper surface o Lower surface a. = XL.46' t o 16.58'.

( c ) Figure 7. - Continued.

0 Upper s u r f a c e o Lower surface a, = 1 7 . 5 8 ' t o 20.59~.

(d)

Figure 7.- ConcLuded.

0 Upper surface Lower surface cc, = -5.10' t o 2.34'.

(a)

Figure 8. - Pressure distributions on wing of model a t free-stream dynamic presslae

of approximately 2840 ~ / m ~ (59.3 lbf /ft2). sf = oO.

o Upper surface

o Lower surface

Figure 8.- Continued.

0 Upper s u r f a c e

o Lower s u r f o c e

a = 12.00~ t o 17.15O.

( c ) Figure 8 . - Continued.

o Upper surface

o Lower surface a = 1 8 . 1 5 ' to 2 1 . 2 2 ' .

(d) Figure 8 . - Concluded.

Wing a =007O, q, = 2/7/newfons/meterz or 4 5 3 5 / b f / f f z

3 I

0 Upper surface Lower s u r f a c e

Figure 9 . - Pressure distributions on wing and flap of model at several

free-stream dynamic pressures. sf = 4 0 ' .

o Upper surface o Lower surface W i n g W i n g Flop 4 I a=-386O a=-4.800 @ 0 0 0 3 0 ~ o

a

0 D q q q O o O o 0 0 I I I I I I a = -4.80' t o 2.17~.

( a )

Figare 10.- Pressure d i s t r i b u t i o n s on wing and f l a p of model a t free-stream ~ n , m i c pressure of approximate* 420 ~ / m 2 (8.8 Ibf/ftZ), 6f = 40'.

o Upper surface Lower surface c /q w/ng

i

a = 4 2 / O 0 0 ~ U 0 0 0 a = 3.18' t o 8.28'.

(b)

Figure 10. - Continued.

o Upper surface o Lower surface Wlng wmg a=9330

lo

5 k 0

0 0 CP ~ O D ~ ~ O O ~

t7 @ I

CL = 9.33' t o 14.33'.

( c ) Figure 1 0 . - Concluded.

0 Upper surface Lower surface

o=-461° o = - 3 5 8 " F'ffp

2 3

0 0 7 ( a ) CL = -4.61~ t o 2 . j 5 5 ° .

Figure U.- Pressure d i s t r i b u t i o n s on wing and f l a p of.model a t free-s-iireaso dynamic pressure of approximately. 1020 ~ / m 2 (21.3 l b f /f t2), 6f = 40@, o Upper surface Lower surface W ~ n g Flop 4 , 7 cr, = 3.56' to 8.75'.

(b)

Figure 1 1 . - Continued.

0 Upper surfoce Lower surface Wing Wing

r

a = /O 68" a ~ 9 . 7 4 ~

I

I

'3

-

r

I

I

0 0 0 0 1 0

0 O , ,

i i?

C , n f 0 2 4 6 8 1 0 0 5 1 0 V c X/c V c ( c ) a. = 9 . 7 4 O to l 2 . 7 3 O .

Figure l l . - Concluded.

FIRST CLASS MAIL

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