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05
00 mim TECHNICAL REPORT 65-73
WIND TUNNa TEST OF 1/7 SCALE MODEL OV-1
I By
F. W. Sh«ph«ard
D«c«mb«r 1965
I. S. AIMY AVIATIIN MATEIIEL UIIUTIIIES
PUT mm, viuiNU
CONTRACT DA 44-177-AMC-271(T)
GRUMMAN AIRCRAFT ENGINEERING CORPORATION BETHPAGE, NEW YORK
Distribution of this document is unlimited. • —;,r
CLEARINGHOUSE FOR FEDBRAL SCJENTIFir AND
TECHNICAL [N^AKMATION Hardoopy Uiotonib»
IALZZL
— •
r
BLANK PAGES IN THIS DOCUMENT WERE NOT FILMED
Disclaimers
The findings in this report are not to be construed as an official Depart- ment of the Army position, unless so designated by other authorized docu- ments.
When Government drawings, specifications, or other data are used for any purpose other than in connection with a definitely related Government procurement operation, the United States Government thereby incurs no responsibility nor any obligation whatsoever; and the fact that the Govern- ment may have formulated, furnished, or in any way supplied the said drawings, specifications, or other data is not to be regarded by impli- cation or otherwise as in any manner licensing the holder or any other person or corporation, or conveying any rights or permission, to manu- facture, use, or sell any patented invention that may in any way be related thereto.
Disposition Instructions
Destroy this report when it is no longer needed. Do not return it to the originator.
ST*
^•v.-«
DEPARTMENT OP THE ARMY U. S. ARMY AVIATION MATERIEL LABORATORIES
Port Eustls, VirginU 23604
This report has been reviewed by the U. S. Axmy Avietlon Materiel Leboretorles end is Judged to be technicelly sound.
The reported effort «es underteken to determine the power-off dreg, lift, end pitching nonent of the OV-1 model, end to exealne the effect of certein eerodyneaic iaproveaents, not es e prelude to nodificetion of the Mohewk es e quentity item, but es e study to better understend flow phenomene essocieted with similer vehicles of this sise end power cless.
The report shows the eircreft to be relatively insensitive to eny chenges short of major redesign. The eree of power effects, such es slipstream, nacelle, engine inlet, end propeller studies, not perforasd on this model, cen be exemined only on lerge-scele powered models.
Consideretion is being given to such follow-on work.
. +, .— _ ■■**-*
Task 1P125901A14203 Contract DA 44-177-AMC-27 1(T)
USAAVLABS Technical Report No. 65-7 3 December 1965
WIND TUNNEL TEST OF 1/7 SCALE MODEL OV-1
By
F. W. Shepheard
Prepared by
Grumman Aircraft Engineering Corporation Bethpage, New York
For
U. S. ARMY AVIATION MATERIEL LABORATORIES FORT EUSTIS. VIRGINIA
DtBtribution of tfti« doemmt is unlimited.
\
SUMMARY
Wind tunnel tests were conducted on a 1/7 scale model of the OV-I air- plane to determine the power-off drag, lift, and pitching moment co- efficients of the model uad Its various components. In standard pro- duction configuration, and with the following modifications:
a. Faired fuselage shape, with canopy removed.
b. Faired nacelles, both with and without cant.
c. Various combinations of tall surfaces.
d. Various fairings.
In addition, tufted flow studies were performed on certain configurations.
The only areas where modifications to the model brought about significant drag changes are the canopy and the nacelles.
• • • in
•mm
CONTENTS
Page
SUMMARY 111
LIST OF ILLUSTRATIONS VI
LIST OF TABLES Vll
LIST OF SYMBOLS Vlll
INTRODUTION
DESCRIPTION OF MODEL
TESTING PROCEDURE
DISCUSSION OF RESULTS
CONCLUSIONS AND RECOMMENDATIONS
DISTRIBUTION 65
APPENDIXES
I. Corrected Coefficients 67
11. Raw Data 74
in. Effect of Transition Strips 87
n .-.♦
. -■
ILLUSTRATIONS
Figure Page
1 OV-1 Moment Transfer Diagram, Model Upright 11
2 Support and Interference Correction to Drag 12
3 l/7 Scale Wind Tunnel Model Drawing, 1/50 Pull Scale Airplane 13
F_ k OV-1 Model, W 2 + F1 + N-L + (T - HVj) 15
5 F1 Fuselage 16
6 F2 Fuselage 17
7 ^ Nacelle 18
8 N2 Nacelle . . 19
9 Flap Brackets 20
10 Wing-Fuselage Fillet U V 21
11 Wing-Nacelle Fillet \W 2) 21
12 Effect of Fuselage, Nacelles Off 23
13 Effect of Fuselag3, N^ Nacelles On 23
Ik Effect of Nacelles, Fg Fuselage 27
13 Model Buildup, F1 Fuselage 29
16 Model Buildup, Fg Fuselage 31
17 Effect of Flap Brackets 33
18 Effect of Fillets . . .' 35.
19 Effect of Fuselage, Nacelles Off 37
20 Effect of Fuselage, N^ Nacelles On 39
21 Effect of Nacelles, Fg Fuselage kl
22 Model Buildup, F^ Fuselage U3
23 Model Buildup, F2 Fuselage 45
vl
"T
-U3 _^ ^
?
Figure
Zk Effect
25 Effect
26 Run 10,
27 Run 10,
28 Run 11,
29 Run 12,
30 Run 12,
31 Run 13«
32 Run 33,
33 Run 31*,
3^ Run 3^
35 Run 35,
36 Run 35,
37 Run 36,
38 Run 37,
ILLUSTRATIONS (Cont)
of Flap Brackets
of Fillets
W + F2 + N2 + (T - HV3), Top View
W + Fg + N2 + (T - HV3), Side View
W + Fi + % + (T - HV3), Side View
W + F-L + Hx + (T - HV3), Top View
W ♦ F1 + H-L + (T - HV3), Side View
W + F2 + N3 + (T - HV3), Side View
T - HVV Top View Fn W ! + F1 + % + (T - HV3), Top View
W ^^ + Fi + % + (T - HVo), Side View F0
3
W 2 + F! + % + (T - HVo), Top View F2 W ^ + F^^ + ^ + (T - HV3)f Side View
w + Pl + Nl + Cr " HV3), Top View
W + F2 + H2 + (T - HVj), Top View
Page
U7
h9
51
52
53
5U
55
56
57
58
59
60
61
62
63
.
Table
1
2
3
TABLES
Incrwental Drag
Run Schedule
Data Reduction Factors and Corrections
Page
5
7
10
vii
V .-.*
f
SYMBOIS r i
w
'2
»I
h "3 T-H
T-H73
T-H72
Standard OV-1 Wing - Short Span Version
Standard OV-1 Wing - Filleted at Fuselage Juncture
Standard OV-1 Wing - Filleted at Fuselage and Nacelle Junctures
Standard OV-1 Fuselage
Modified (Faired) Fuselage
Standard OV-1 Nacelle - Production Cant
^ With Faired Ellipsoid Nose
1^ With Zero Cant
Horizontal Tall
Horizontal Tall + Center Fin and Rudder
Horizontal Tall + Tip Fins and Rudders
Horizontal Tall + Center + Tip Fins
1.8. unage System
STAT Wind Off Test for Static Balance Forces
q, > UO Wind on Test at Utacorrected Tunnel tynamlc Pressure of ho p.s.f.
•
S
CL
%
AC
Wing Area - square feet
lift Lift Coefficient -
Drag Coefficient -
qs drat
qs
Increment of Lift Coefficient
Increment of Pitching Moment Coefficient
Slope of Lift Coefficient versus Angle of Attack
vlll
L^- :- —
DTTRODOCTION
This report, submitted in compliance with Contract DA Mf-177-AMC-27l(T), presents the results of wind tunnel tests of a l/7-scale unpovered model of the QV-1 airplane. The tests were conducted In the Grunman Aircraft Engineering Corporation 7- hy 10-foot subsonic wind tunnel during the period from 1 June to Ik June 1965.
The tests were run to determine the pover-off drag, lift, and pitching moment coefficients of the OV-1 model and its various components at the request of the U, S. Array Aviation Materiel laboratories.
W~'l
1 .<
DESCRIPPION OF MODEL
The model tested was a l/7-scale unpowered model of the production (short wing) OV-1. A three-view drawing of the model is Included as Figure 1, and a typical photograph of the model Installed in the wind tunnel is shown as Figure 2.
The symbols describing the various model components are explained in Table II. Sketches of the streamlined (Fg) and production (Fj) fuselages are shown in Figures 3 and 4; and sketches of the streamlined (No) and production (N^) nacelles are included as Figures 5 and 6. Note that the production nacelles Incorporated flow through, witti no attempt made to control or measure the mass flew.
Transition was fixed on all surfaces for all runs by means of "pinked" plastic electrical tape - a typical installation is shewn in Figure 2. To define the effect of these transition strips on drag values, additional tunnel runs were performed. Data from these tests are presented as Appendix III.
The flap brackets shewn in Figure 7 were on the model for all runs except where the bracket Increment was measured.
The wing-fuselage and wing-nacelle fillets which were tested cure depicted in Figures 8 and 9*
TESTIMG FROCEDURE
The test program consisted of the runs listed in Table 2. The model was pitched through an angle of attack range from -6 degrees to stall plus 2 degrees in 2 degree increments except near the stall where the data was taken at 1 degree increments. All force data was measured at a dy- namic pressure of kl,l pounds per square foot (corrected for blocking). The nominal test Reynold's number RN ■ 1.186 x 10° per foot, which, ad- justed for a wind tunnel turbulence factor of 1.36 yields an effective Reynolds number of 1.612 x 10^ per foot.
DATA REDUCTION
All data were reduced to standard N/VSA coefficient form using the factors presented in Table 3« The data were corrected for support tare and interference wind tunnel flow alignment. All moments were transferred from the balance resolving center (trunnion point) to a model center of gravity located at fuselage station 159.5 and water line 80,9. The transfer diagram Is shewn on page 11.
No correction for internal drag has been made to data obtained with the 0V-1 (F1) nacelle. Further, none of the data were adjusted for the flap bracket Increment. It should be noted, however, that the increment due to brackets was determined and is shown on Figure 15.
IKESEREATIQN OF DATA
The foise data, corrected, transferred, and reduced to standard NASA wind axis coefficients, are listed In Appendix I, pages 65 - 71. The raw balance data, recorded to a base of 50,000, from which the coefficients were derived are listed on Appendix II, pages 72 - 8U.
Plots of the final data are presented as a function of angle of attack In Figures 10 to l6, and as a function of lift coefficient In Figures 17 to 23.
The tuft study photographs are included as Figures 2k to 36.
•V i
\
\_»
DISCUSSION OF RESULTS
Table I Indicates the increments In drag due to configuration differences. In general, the increments were taken at a C-^ of 0.600, however, where configuration differences were taken between a tail-on and a tail-off run, the increments were taken at an angle of attack where the tail-on and tail-off pitching moments crossed (where äCm, and consequently ACL due to tail was zero).
In general, the data indicate that:
1. The canopy fuselage has 0.0020 CD higher drag than the streamlined nose.
2. Uncanting the streamlined nacelles accounts for only 0.0010 C^.
3. The complete tail assembly adds 0.0060 0^.
h. The 0V-1 nacelles (with flew through) have 0.00^5 to O.OO55 higher C-Q than the uncanted streamlined nacelles (without flow through).
5. Although the fillets appeared to cause some flew improvement a drag improvement of only 0.0010 CD is indicated from the force data.
A brief comparison of the data with theory indicates that the angle for zero lift checks at -2 degrees, the lift curve slope is in reasonable agreement (test Cr^ = O.OfJO, theoretical Or = O.0T6O to O.0T7O, depend- ing on whether smooth or rough section Cj_ u used), and Oswald's effi- ciency factor "e" was measured to be 0.8TW to 0.8800 dependent on config- uration which also compares reasonably with the theoretical value of 0.9100.
(0
H s O •H +> •H
3
vo
S
<3 ® O +
O +
7
00 (0
•p
0) +» o (U u 8
lf\ IfN
o +
o +
t>0 CO
^ H •H
H
s H.5
Vl O <U II -P +» 5 ö a
43 TJ u CO _
a BJ6
5 •0 ^ 0)
S 50 o ^ 0) ■ä S» F-i d 8 <u to O
e (u ^ o 0) 0) a>
8 Ö o +
GO
8 o +
7 + +
fe h fa h h h fa +
> > > > + +
i
or»
7?^^? ^ fa +
H PCVI .CVI .CU fa fa fa fa
+ + H
+ + + + fa +
fa +
I II 1
O +
li
CO
(0
a> a» a>
o H 8 o +
o o + +
n m n J t i
r»H + fa
fa + + * .
+ +
+ + »r 7
«.W r.^ «^ fa fa fa +
Jl .. .J
s1 feH sw 6m eT ■ i
*[* if* if* tf* if* + + + + + .CVI .CVI CVI rCVI „.CVI fa fa fa fa fa + +
Jl—I
+ +
cJNCLUSIONS AND RECOMMEaffiATIONS
The only areas for which significant drag differences were measured were in the canopy area and nacelle area. It should be noted, however, that reductions in frontal and wetted areas accompanied the streamlining of the fuselage thereby accentuating the effect of streamlining. The incre- ment in drag assigned to the OV-1 nacelles configuration is also not real- istic since the mass flow through was neither controlled or measured, and thus internal drag could not be accounted for. In addition, the air- plane nacelle-wing area is imaersed in a slipstream which is not represent- ed by power-off testing. It is thus recomnended that further investigation of nacelle drag be conducted with a powered model instrumented for thrust and mass flew measurements before conclusions regarding nacelle drag are drawn.
Tunnel Run No,
1
2
3
5
6
TABLE 2 RUN SCHEDULE
Configuration
W + F2 + N (Inv)
W + F2 + N (inv) + I.S.
W + F2 + N + I.S.
Run Type Remarks
STAT
q = UO
STAT
q = UO
STAT
q = UO
Tare, Inter- ference & Alignment Rune
7
8
9
10
11
12
13
Ik
15
16
17
18
W + F2 + N3
W + F2 + N2
W + F2 + N2 + (T-HV3)
W + Fl + Nl + ^"^3^
W + F1 + N^ + (T-HV3) degrees CANT
W + F2 + N3 + (T-HV3)
W + F.
W + F2 + ^
W + F2 + ^ + (T-H)
- 0
STAT
q = ^0
q = IfG
STAT
q = UO
q = 1^0
STAT
q = UO
Nacelle
Variation
Tuft
Runs
Model
Buildup
F2 Fuselage
_. \.
TABLE 2 (continued)
Tunnel Run No. Configuration Run Type Remarks
19 W + P2 + B^ + (T-HV^ STAT
20 q = UO (cont'd)
21 W + F2 + ^ + (T-HV2) STAT Model Buildup
22 q, = kO P2 Fuselage
23 W + F2 + Nl + (T-HV3) STAT
2k q = 1+0
25 V + -F1+V1 + (T-HV3) STAT
26 q = kO Model Buildup
27 W + F1 + N STAT F1 Fuselage
28 q, = kO
29 W + F^^ STAT
30 q = UO
31 W + F. (Flap Brackets Removed) STAT Effect of
32 q = UO Flap Brackets
33 T-H7 Tuft
3^
35
V*1 +T1+ ^
^ + Fj^ + ^
+ (T-HV )
+ (T-HV ) Runs
36 W + Fl + Nl "H (T-HV3) Repeat Tuft
37 W + F2 + N2 + (T-HV3) Runs
8
Tunnel Run No.
38
39
ko
hi
TABLE 2 (continued)
Configuration
W1*1 + F1 + ^ + (T-HV )
W1"2 + ^ + 1^ + (T-HV3)
Run Type Remarks
uxnx Effect
q = UO of
STAT Fillets
q = 40
rwilP"
TABLE 3 DATA RiDUCTION FACTORS AMD CORRECTIONS
Model Dimensions
Wing Area (S) = 6.735 square feet
Wing Span (b) = 6.000 feet
Wing Chord (c) = 1.170 feet
Moment Transfer Diagram - Rage n
Moment Transfer Equation
:m = Cn. " CT "T" S±n (P " «) " C^ ^- COS (P - <*) mc iUpp L c Dc g
= C - 0.1119 [CL sin (0 - o) + C cos (ß - a)l '"TR
Tunnel Wall Corrections
4 »(DUO) ' 0•7l,50 0L
- 0.0110 c,2
L A C,
A C m = 0.02^5 CT (applied to Tall On data only)
Blockage Correction
q corrected = 1.0281 q uncorrected
Support and Alignment Corrections
A or = -K).0300 degrees
A C = +0.0025 m
A C-,4 = 0,0Ökl CT Dalign L
"De upport - ftige
10
T
FUSSTA 159.5
CG @ u = 0°
WL 100 FRL
CG@ CC = iW=1.5#
TRUNNION POINT
DIAGRAM: FULL MODEL SCALE - DIMENSIONS IN INCHES
Figure 1. OV-1 Moment Transfer Diagram, Model Upright.
11
__-V--»
o o
o
(O
CJ
00
b
i <
I 1 Ü 4)
s
oo
8
a |
i i I 1
I
12
"* ■ a%^p|fr^afe ^ A-
Figure 3. 1/7 Scale Wind Tunnel Model Drawing. 1/50 FuU Scale Airplane.
13
A
4. T T' 2
CT« 4.757-
cT»s.aoo
Z WL 95.5
-MOC» 7.071
■M0C«5.S2I
12.857
J.I82
Cn« 7.571
t CjtftOOO
(NACA 2412)
CR «18.000 (NACA 2412)'
B i:
^
NOTE: DIMENSIONS IN INCHES MODEL SCALE
-AILERON HINOE {. AT TIC
•<0.07l
AREA A.R. T.R. SWEEP® 0.40C.
CR CT SECTION DIHEDRAL INCIDENCE FLAP AREA (TOT DROOPED AILER( AILERON AREA (J L.E. SLAT AREA
VL
AREA A.R. SWEEP® 0.55C. T.R.
CR CT
SECTION RUDDER AREA
Vt
AREA A.R. SWEEP® 0.60C. T.R. CR C'j SECTION RUDDER AREA
AREA A.R. SWEEP® 0.75C. T.R.
CR C'T
SECTION DIHEDRAL ELEV. AREA (TC
"har T
t
iioc««.ori
1 WING
AREA 6.734 ft.2
A.R. 5.35 T.R. 0.5 1 SWEEP® 0.40C. 08 j CR 18 inches CT 9 inches | SECTION NACA 2412 DIHEDRAL 68 30' INCIDENCE V 30' 1 FLAP AREA (TOTAL» 0.889 ft.2
DROOPED AILERON ARK A (TOTAL) 0.357 ft.2
AILERON AREA (TOTAL) 0.463 ft.2
0.836 ft.2 L.E. SLAT AREA (TOTAL)
VERTICAL TAIL (OUTB'D) j
AREA 0.438 ft.2 (each) A.R. 2.06 SWEEP @ 0.55C. 0° T.R. 0.46 CR 7.571 inches CT 3.500 inches SECTION NACA 0012 RUDDER AREA 0.197 ft.2 (each)
I VERTICAL TAIL (CENTER) j
AREA 0.526 ft.2
A.R. 1.64 SWEEP® 0.60C. o* T.R. 0.54 CR 8.785 inches
^T 4.757 inches SECTION NACA 0012 RUDDER AREA 0.231 ft.2
HORIZONTAL TAU. |
AREA 1.734 ft. A.R. 2.65 SWEEP® 0.75C. 0* T.R. 0.5 cR 12.942 inches C'p 6.471 inches SECTION NACA 0012 DIHEDRAL 6* 30' ELEV. AREA (TOTAL) 0.459 ft.2
D l.
Figure 4. OV-1 Model, W + F, + N1 + (T - HVg).
15
r
\
CANOPY NOSE - TYPICAL SECTION
CANOPY NOSE
Figure 5. F Fuselage
16
u
• -* -«
I1
■I
CLEAN NOSE - TYPICAL SECTION
CLEAN NOSE
Figure 6. F2 Fuselage
17
__\, ■♦
LE WING-(REF) TE WING-(REF)
Figure 7. N Nacelle.
18
-» » — ■ ■ ■ m
I LE WING-(REF)
TE WING-(REF)
i
Figure 8. N Nacelle
19
r
\
I
1 I
\
Figure 9. Flap Brackets.
20
■■■M «i ■ '
k
Figure 10. Wing-Fuselage Fillet (wF0.
Figure 11. Wing-Nacelle Fillet (wF0.
21
~ T
Z0- 10- 0 10
.
A v »
es
JJO saxiaDBN • aSBidsnj jo ^oajja * ZI 9xnS\d
jo 9\iuy ' »
B w~~i
20
16
1.0 0.8 0.6
12
0C , Angle of Attack, Degrees
_ _ 1 <
o-o*. ^^ ̂ ^^^
^5
\
"X X. T V
N V '
^
\
\
s X v ^
\
1
1
} ■i
/
0.18 0.16 0.14 0.12 0.10 0.08 0.06 0.04 0.02
CQ, Drag Coefficient
Figure 13. Effect of Fuselage, N Nacelles On.
25 A
C , Pitching Moment Coefficient no
B
Mi
cc, Angle of Attack, Degrees
Figure 14. Effect of Nacelles, F Fuselage.
A i. i
C , Pitching Moment Coefficient n
B T"
GC, Angle of Attack, Degrees
0.18 0.16 0.14 0.12 0.10 0.08 0.06 0.04
CD, Drag Coefficient
0.02 0
Figure 15. Model Buildup, F Fuselage.
29 A L
^ CL' Lift Coefficient
0.* 0.2 0 -0.2 -0.4
OV-1, 1/7 Scale 1
— c Series 1
Symbols Run ^ x" ^—
o 30
28
W + Fj p /
1 D
/ »,
-
0 26 W . Pj + Nj * (T- *** ) /] s
>^
»- K w /
1
1 ^ ^J s^ /
1 >d
^N s- /
^^ / { 0.1 -0.1 -0.2 -0.3 -0.4
Cm, Pitching Moment Coefficient
B fp- r
24
20
16
12
a , Angle of Attack. Degrees
-4
^
1.0 0.8 0.6
0.18 0.16 0.14 0.12 0.10 0.08 0.06 0.04 0.02 0
CD, Drag Coefficient
Figure 16. Model Buildup, F Fuselage.
31 A
< CL, Lift Coefficient
6 0.4 0.2
Cm, Pitching Moment Coefficient
B ,. m.-■.
20 1.0 0.8 0.6 I o.g
16
12
a, Angle of Attack, Degrees
0
^
v
V \
^ \
X ■^^
%
\
^ X 1 ^5
\
* i
B
/J 1
0.18 0.16 0.14 0.12 0.10 0.08
CD, Drag Coefficient
0.06 0.04 0.02
Figure 17. Effect of Flap Brackets.
33 A fr^"
CL, Lift Coefficient
0.02
I 0. 6 0.4 0.2 ( ) -0.2 -0.4
OV-1, 1/7 Scale
1
Series 1
Symbols Run ■
k. o 30 W + F Brackets On *K >l. I u
X ̂« x 32 W + Fj Brackets Off
i ii \ N V \ } Vv \
N w
XJ s. \ w X. J N ̂
\ \ A j I
I X. \
Jl N. \
0.1 -0.1 -0.2
Cm, Pitching Moment Coefficient
B '
24
20
16
12
OC. Angle d Attack, Degrees
-8
1 0 0.8 0.6 ] 0. 6
1 ^
c -=
1
% ̂
"^
T
\ ■s ̂ j 1
N L
V V J ^ V
N v 1 /
/
|
0.18 0.16 0.14 0.12 0.10 0.08
CD, Drag Coefficient
0.06 0.04 0.02
Figure 18. Effect of Fillets.
35 A U
C., Lift Coefficient
6 0.4 0.2 0 -0.2 -0 .4
OV-1. 1 7 Scale Series 1
1
Symlx
0
•Is Run
26
39
41
W ♦ Fj ♦ 1
Fl W ♦ Fj
F2 W * ♦ Fj
^j + (T - 1
♦ Nj ♦ (T
♦ Nj ♦ (T
"4 ^
.^
a
- HVj)
■ HV3)
/
Y 1 /
k /
/
/
"N /
\^
w
0.1 -0.1 •0.2 -0.3 -0.4
C , Hitching Moment Coefficient m
B
1.2
1.0
0.8
0.6
C, . Lift L 0.4 Coefficient
0.2
-0.4
-8
0C, Angle of Attack, Da|( /
0 4 8
0.02 0.04 0.06 0.08 0.10
C-, Drag Coefficient
0.12 0.14
Figure 19. Effect of Fuselage, Nacelles Off.
37 A
I Attack, Degrees
3 12 16 20 24
> JA ̂ «
OV-1. 1/7 Scale Series 1
/ /
\
•
/ \\
/ \\
1 1 Symbols Run
« 15 W + F-
/
r
\ \
o 30 \ V + Fl
/
\
1 ^ \
;
l 0.2 0.1 0 -0.1 -0.2 -0.3 -0.4 -0.5
C , Pitching Moment Coefficient m
B
\-
1.2
1.0
0.8
0.6
CVUtt 0.4 Coefficient
0.2
-0.2
•0.4
-8
OC, Angle of Attack, De A
0 4 8 r*H
s F= j------^0^ ti- o -
y /*-
/
/
/
r
> /
/
/
•
/ /
* -
/
/
/
\ / /
1
\ c /
4
«
0.02 0.04 0.06 0.08 0.10 0.12 0.14
CD, Drag Coefficient
Figure 20. Effect of Fuselage, N Nacelles On.
39 A
J i 2 16 20 24
! i
OV-1. 17 Scale Series 1
1 n 1
4 ^
^
ys*^ ! r
f . / i Symt
n
>ols Run
16
28
W + F2 +
W + Fj +
N 1
/
r □
1
Nl
Y
1 i
1
9
h I ♦ i i !
0.2 0.1 -0.1 -0.2 -0.3 -0.4
Cin. Pitching Moment Coefficient
B ■0.5
V
OC , Angle of Attack, Degra
CL' Lift 0.4 Coefficient
0.02 0.04 0.06 0.08 0.10
CD, Drag Coefficient
0.12 0.14
Figure 21. Effect of Nacelles, F2 Fuselage.
hi A
jri Attack, Degrees
$ 8 12 16 20 I
s S^1 w OV-1. 17 Scale Series 1
i C- O
\jfcz p**^ 1 F 'A
\ \
\ X
\
]/ f
IV \ \ f \
Symbols i i i
Run
i B * X 15 W * F2
■
\\ C 5
)
16 W + F2 .
9 W + F2 ^
h N.
6i c
1 1
. N2
I t 8 W ♦ F2 ^ ̂N3 1
V 0.2 0.1 -0.1 -0.2 -C.S -0.4
C , Pitching Moment Coefficient m
B
-0.5
a , Angle of Attack, Deg:
0 4 8
Coefficient
0.04 0.06 0.08 0.10 CQ, Drag Coefficient
Figure 22. Model Buildup, F Fuselage.
^3 A
24
OV-1, 1/7 Scale Series 1
*4±
Symbols Run
O 30 W vF-
a 28 W ♦ F. ♦ N.
0 26 W ♦ Fj ♦ Nj ♦ (T - HV3)
0.2 0.1 -0.1 -0.2 -0.3 0.4 -0.5
C . Pitching Moment Coefficient m
B
CL. Lift
Coefficient
OC, Angl e of Attack, H k, Degi
- 8 4 ( ) 4 8 ^ 8
1.2
1 •
^
k
1.0 A^l ̂ Ü
^ ^
B^^1
»■ v
A
0.8
0.6
0 4
^ r i I
J r /
r I f- / / y /
Syj
-
Syi
7 f
/
0.2
. A ' ■ — •
0
0.2 [ ^
k "^ — —
0.4
1 ±- C
—< /.
C 0.( )2 0.( M 0.( »6 0.( )8 0. 0 0. 2 0.1 14 — ~^
CD, Drag Coefficient
Figure 23. Model Buildup, F Fuselage.
^5 A
\
»egrees
12 16 20 24
OV-1, 1/7 Scale
/
^
^
<] < r f f^
Series 1
Symbols Run
16
.'
\|
o W ♦ F2 ♦ N. nn\ A 18 W ♦ Fj ♦ Nj ♦ (T - H)
/ 71 \ 0 20
22
W ♦ F. ♦ N- ♦ (T - HVj) .
W ♦ F. ♦ H. ♦ (T • HVa)
/// \
0 m \ o 24 W ♦ Fj ♦ Nj ♦ (T - HVj)
i i i 1 \
w \
\ 1
/j f \
1 f*
0.2 0.1 -0.1 ■0.2 -0.3 •0.4 -0.5
C , Pitching Moment Coefficient m
B
CL. Lift 0 4
Coefficient
OC , Angle of Attack, Dritttack,
0 4 8
r
0.04 0.06 0.08 0.10
Op, Drag Coefficient
0.12 0.14
Figure 24. Effect of Flap Brackets.
47 A
k. Degrees
8 12 16 20 24
rr< h-o
OV-l. 1 7 Scale Series 1
rO-O 1
1 A f
\
/ \
/ \ 1 II
| Symbols Run j
/ \\ [ 0 SO W ♦ Fj Brackets On |
/ / \ « 32 W ♦ F, Brackets Of
/
* *
\
\
t
\
v
\ 1 I
\
\
0.1 -0.1 -0.2 -0.3 -0.4 -0.5
C_. Pitching Moment Coefficient
B
1
i ». r
- .. _ ^^ »..— - *
at, Angle of Attack, Dt]
1.2
1.0
0.8
0.6
CV^ 0.4 Coefficient
0.2
•0.2
•0.4
0.2 0.4 0.6 0.8 C-, Drag Coefficient
Figure 25. Effect of Fillets.
1.4
A
lm..*M _ ttm T -
Utack, Degrees
8 12 16 20 24
1*4 n n OV-1, 1/7 Scale
j/j*^ Series 1 1 /«^ 1
1 1 / f\ i/ / r w
M jl Synt bols Run
0 26
» 39
D 41
W ♦ Fj •♦
W * ♦ Fj
W 4 ♦ Fj
Nj ♦ (T -
l ♦ Nj ♦ (1
l ♦ Nj ♦ (1
HV3)
' - HV3) |
' - HVj)
1
1 J *
i
0.2 0.1 -0.1 -0.2 •O.S -0.4 -0.5 Cm, Pitching Moment Coefficient
ex: = 10. 7°
ex: = 12. so
ex: = 6. 5° ex: = 14. so
Figure 26. Run 10, W + F 2
+ N2
+ (T - HV 3), Top View.
51
a: = 10. 7°
a: = 12. so
a: = 6. 5° a: = 14. so
Figure27. Run10, W + F2
+ N2
+ (T- HV3
), SideView.
52
C( = -4. 1°
cc = o. r C( = 10. 7°
C( = 12. so
C( = 6. 5° C( = 14. so
Figure 2S. Run 11, W + F1
+ N1
+ (T- HV3
), Side View.
53
a: = 10. 7°
a: = 12. 8u
a: = 6. 5° a: = 14. 9°
Figure 29. Run 12, W + F 1
+ N1
+ (T - HV 3
), Top View.
a: = -4. 1° a: = s. 6°
cc = o. r C( = 10. 7°
a: = 12. so
C( = 6. 5° C( = 14. so
Figure30. Run12, W + F1
+ N1
+ (T- HV3
), Side View.
55
ex = -4. r
ex = 10. 7°
ex = 12. go
ex = 6. so ex = 14. go
Figure 31. Run 13, W + F 2
+ N3
+ (T - HV 3
), Side View.
ex: = -4. p
ex: = 6. 5°
ex: = 8. 6°
Figure 32. Run 33, T - HV 3
, Top View.
57
z*
'- ^ ** . - -, ^,- «fc
\
ä = -4. r a = 8.6°
OC = 0.1° a = 12.8°
OC = 6.5° OC = 14.8°
Figure 33. Run 34, W + F + N + (T - HV ), Top View. " 1X9
58
■.<:
^— - -
K-..,, - IMM
a = -4.r
oc = o. r
cc = 4. 4°
8.6°
10. 7'
CC = 12. 8°
\
« = 6.5# OC = 14. 8*
Figure 34. Run 34, W 1 + F1 + Nj + (T - HVg), Side View.
59
.•..» .
\ \ -
«m wrm
i cc = -4. r
oc = o. i*
a = 4.4'
a = 8.6°
OC = 10. 7e
ägm^mm
a = 12.8°
OC - 6.5' OC » 14. 8°
F. Figure 36. Run 36, W + F1 + N + (T - HV ), Top View.
60
tl
^i-»' ' ■
-■V
OC = -4.1° OC = 8.6°
■ 1 b E"- -V/ ^
HIM R&- 1 m-:--lS
m
V.
a - o. r 10. ?•
0C = 4.4° a = 12.80
a - 6.5° a = 14.8*
Figure 36. Run 35, W + F1 + N1 + (T - HV ), Side View.
61
.-.*
!
!». JJJMi'MH.-^U —^^ '■— ■»
v\.
OC = -4.1°
<r = o. r
cc = 4.4°
OC = 8.6°
OC e 10.7°
a = 12.8*
I
OC = 6.5° OC = 14. 9°
Figure 37. Run 36, W + F + N + (T - HV_), Top View. 11 o
62 i , I
I* J»- „ -
oc = -4.r
oc = 0.1°
a s 4.4°
a = 8.6°
OC - 10.7*
OC = 6.5° a = 14.8°
Figure 38. Run 37. W + F2 + N + (T - HVg). Top View.
63
DISTRIBUTION
US Army Materiel Command 8 US Army Mobility Command 5 US Army Aviation Materiel Command 9 Sixth United States Army 2 United States Army, Pacific 1 USA COMZ Transportation Command (Prov) 2 United States Army, Hawaii 1 United States Continental Army Command, Fort Rucker 2 Chief of R&D, DA 1 US Army Aviation Materiel Laboratories 20 US Army R&cD Group (Europe) 2 US Army Limited War Laboratory 1 US Army Research Office-Durham 1 US Army Test and Evaluation Command 1 US Army Medical R&D Command 1 US Army Engineer Waterways Experiment Station 1 US Army Combat Developments Command, Fort Belvoir 2 US Army Combat Developments Command Experimentation Command 3 US Army Command and General Staff College 1 US Army Transportation School 1 US Army Aviation School 1 Deputy Chief of Staff for Logistics, DA 1 US Army Infantry Center 2 US Army Aviation Maintenance Center 2 US Army Aviation Test Board 3 US Army Arctic Test Center 1 US Army Electronics Command 2 US Army Aviation Test Activity 2 Air Force Flight Test Center, Edwards AFB 1 US Army Field Office, AFSC, Andrews AFB 1 Air Force Flight Dynamics Laboratory, Wright-Patter son AFB 1 Systems Engineering Group (RTD), Wright-Patterson AFB 2
Bureau of Ships, DN 1 Bureau of Naval Weapons 6 Office of Naval Research 2 Chief of Naval Research 2 US Naval Air Station, Patuxent River 1 US Naval Air Station, Norfolk 1 David Taylor Model Basin 1 Ames Research Center, NASA 1 Lewis Research Center, NASA 1 Manned Spacecraft Center, NASA 1 NASA Representative, Scientific and Technical Information Facility 2
65
■a i
Research Analysis Corporation 1 v ( NAFEC Library (FAA) 2
Electronics Research Laboratories, Columbia University 1 US Army Board for Aviation Accident Research 1 Bureau of Safety, Civil Aeronautics Board 2 US Naval Aviation Safety Center 1 Federal Aviation Agency, Washington, O. C. 1 The Surgeon General 1 Defense Documentation Center 20 US Patent Office 1
66
x.
APPENDIX I CORKECTED COEFFICIENTS
RUN 8
i
AXIS ANGLES ÄTTTCIT W -06.19
w
W
W TT W TT w I-
w W w
öRUHMAN LöW FORCES
YÄW~
■Ö4.Ö7 •01.95 inrrrr 02.28
10.76 11.Sl 12.85
1»»89 15.69 16.88
06.53 ■sntr
rrrr 00.00 -00*3046
SPEED WIND TUNNEL TEST NO 0210Z MOMENTSZ
PITCH
AXIS
ÖÖ.ÖÖ 00.00
•00*1436 00.0158
DRAG 00.0282
~5Tüe— 00.0010 -00.1189
00.00 00.00 00.00
00.177& 00.3465 00.5147
00*0231 00.0217 00.0239 00.0306 00.0407
00.0010 00.0007
•00.0003 -00.0014 •00.0003
-00*1044 -00*0888 -00*0784 -00*0569
YÄW ROLL 00*0016 00*
RUNZ 0003
00*00 00*9626 00.0923 -00.0010 00.00 00.00 00*00
01*0523 01*1046 01*1219
ÖÖ.1Ö&5 00.1300 00.1639 00*0090
00*00 01*1645 00.1651 -00.0191 -00*0119
00*0000 00*0014
•00.0158
•00*0406 00*0049 00*0106 00*0027
60*6018 00*0019 00*0021
TO 00* ^7
0000 ÜÜÜT
00*0025 -00*0003
00.00 00*00
00*0029 00.0019 00.0027 00.0031
00* 00* 00* 00*
0005 0011 OTT? 0153
01*1564 01*1508
00.2059 00.2406
•00*0133 00*0000
-00*0090 -00*0193
00*00 00*00 00*00
01*1620 00*6794
00*2630 •00,0026 •OtftWQ?
•00*0236 •Mt92»»
00*0025 00*0013 00*0006 OOtOQK
00* 00*
0044 0055
00* 0066
00*8411 00.0716 -00*0016 -00*0067 00.0022 -00*0001
008Z 00*0016 00*0003 0082 00.0016 »00*0003 008Z
008Z 0082
"OMI 008Z 0082
.0082 008Z 008Z 0082 008Z 0082 0082 008Z
RUN 9
,x'? am M -06.19
GRUMMAN LOW FORCES
SPEED WIND TUNNEL TEST NO 021QZ MOMENTSZ
AXIS
YAW LIFT 00*00 -»00*3075
DRAG SIDE PITCH YAW ROLL RUNZ * 00.0269 -00.0003 -00.1196 00.0013 QQ.QQQ4 Qfi2£
W w V w
•04.08 »01.96 00.15 02.28
00.00 00.00
•00*1460 00«0122
00*0238 00.0224
00*0000 •00«00Q7
•00*1057 •00«069S
00*0012 Q9.QQ13
00*0001 QQ'OQQi
009Z 0092
W w i" w r w
w B" w r
04.40 06.52
00.00 00.00 00*00 00*00
00*1740 00*3436
00*0249 00'Q3Q6
•00*0007 •OQtOQl»
•00*0746 •PQtO»?
00*0014 OQtQQl?
00*0000 OQ'OQQQ
009Z QQU
00*5062 00*6665
00.0416 00«05»5
•00*0003 'PPtPOQT
•00*0411 00*0017 00*0001 009Z 0Q92
08.64 0*75
00.00 00*00
00*8223 00*9766
00.0719 00.0940
■00.0021 »JUUflflU
-00*0112 AflAflflfta
00.0016 QQiQ022
•00*0001 •QOiQOQä
0092 QQ92
1.80 2.82 TXT 4.87
00*00 00*00 00*00 00*00
01*0465 01*064^
00.1089 00.1423
•00*0003 OQtOPQ?
00*0031 00*0017 00'0Q12
-00*0006 009Z OQ?Z
01*1053 01*1306
00.1630 00.1608
•00*0003 00*0003
•00*0059 •90»9Q?7
00*0010 oo«QOiQ
00*0045 QQ»QQM
009Z
TTTT 6.90 T^9"
16.67
00.00 00*00
01*1360 01*1732
00.2060 00*2274
•00*0064 •PQtQQB»
-00*0090 •9P»QQ^
00*0011 00.0015
00*0022 00*0013
009Z mi
00*00 09t99
01*1613 01*1400
00.2546 00.2645
•00.0039 ■00.0176
•00*0152 -00.0463
00*0014 MlOQ»
00*0022 QOiQoaa
009Z Mil
67
RUN 15
AXIS ANGLES ATTACK
GRUMMAN LOW SPEED .WIND TUNNEL TEST_NO 02102 FORCES MÖMENTS2
YAW LIFT DRAG SIDE PITCH YAW ROLL RUNZ
AXIS
»
W -06.20 W -04.08 W -01.97 W 00.14
02.«" 04.38 06.50 08.62 10.73
W w M W W" W IT" M W " W w~~ w
11.79 T2V84- 13.88 14.92 15.96 16.93 17.95
00.00 00.00 00.00 00.00
"CTÖ.OO" 00.00 00.00 00.00 00.00 00.00 00. 00 00.00 00.00 00.00 00.00 00.00
•00.3119 •00.1595 •00.0021 00.1573 ■0*0."J1T6~ 00.4822 00.644ir 00.7978 00.9508 01.0201_ 01.0880 01.1515 01.2071 01.2490 01.2086 01.2367
00.0246 -00.0010 -00 00.0195 -00.0028 -00 00.0180 -00.0014-00 00.0197 -00.0021 -00
■W7ÖT4I -ÖÖ.ÖÖ~ 00.0333 -00.0014 -00 ÖOV
• 1181 ^1063 .0957 .0834 i( .0579 .0451" •0322 .0170 .0090
00*0012 _00.0013 00.0013 00*0013
TRJToTSIi ^0^0015 00.0015 00*0015
-00.0016 _^00.0012_ -00*0017
^O0.*0010 -00*0015
^0_0*0011 -ÖO.ÖOIA -00.0015 -00.0017 -00.0015
-00.0036 -00 00.0605-0 Oj. 0 0 2 5_- 00 ÖÖ70785 -0Ö.ÖW6 -00.0170 00*0015 00.0887 -00.0032 -00.0090 00*0015 00.0"97?5~=00.00?8 -00*0013 ÖÖ*0015 -00*0015 00.1095 -00.00?5 00.0078 00*0016 -00*0006 00.1214 -OÖVOÖI? W*öHni ÖOiÖÖIl -00*0007 00*1318 -00.0014 00*0234 00*0012 00*0000 00*1624 0Ö7&12~9 -00*0124 -00*0028 ÖÖ«0076 00*1847 00.0115 -00*0201 -00*0025 00*0096
015Z 0152 0152 015Z 015Z
_015Z 0152 0152 Öl 52 0JL?Z "0152 0152 0152 015Z ÖlSZ 015Z
RUN 16
AXTS^NSL^S ATTACK
GRUMMAN LOW SPEgD WIND TUNNEL TEST NO 02102 FORCES MOMENTSZ
YAW UFT DRAG S1£L PITCH YAW
_ÄÄIS
JMkL. ftUftt-
w w w' w 9' w r w r w
-06.20 -04.09 ^T*-97 00.14 02*26 04.39
08.62 TÜ773" 11.77
00.00 -00 00.00 -00
"ÖO.OO -00 00.00 00 00.00 ÖÖ 00.00 00
3191 1612 oofo' 1581
00.0322 00^0270 00.0249 00.0273
•00.0010 ■00^0018_ •00.0014 •oo»oo?i
-00.1182 •00.1044 •00.0887 •00«o7?9
00*0013 00*0013 00*0013 OQt.QOlfr.
•00*0018 •00.0023 •00*0024 ■QQiQ026
0162 _0WZ 0162
.0162
W W W W «" W
w
12*SÖ 13*81 14*84 15.86
T6.88 17.89
19*86
3169 4866
00.0332 00.0431
00.00 00 00.00 00
00.00 01 öö.öö oT 00.00 01
6483 8028 948T 0024
0541
00*0548 00*0715
•00.0025 •00.0021 •00.0025 •00.0018
•00.0573 •00.0414
00*0015 00*0015
■00.0254 •00.0093
00*0017 00*0017
•00*0025 •QOtOOlP
00.0918 00.1106
•00*0023 •00*0021
•00.0021 •00.0032
00.0030 00.0026
oo.oö or 00.00 01
irö*T>ö oi 00.00 01
1,172 1436 1548 IsTT 1187
•00.0043 •00.0090
•00.0021 •00.0148
00.1346 00.1695 oo.m« 00*2083 00*2262 -00.0111 -00.0118 C0.2461 -00*0158 -00*0161
00*0021 00*0023 00*0020 00*0006
•00*0014 00.0019 00*0038 00*0061
•00*0086 •00.0101
•00*0163 •00*0135
00*0004 00*0001 00*0008 00*0018
00*0054 00*0038 00.0024 00*0021
0162 J).L6Z 0162 OlßJ. 0162
JSOAl 016Z 016Z 016Z 016Z 016Z UM
00*00 01 00.00 01
00*2812 00*3053
•00*0209 00*0162
•00*0457 •00*0543
00*0036 •00*0040
00*0052 oo*oo»*
0162 -OUZ
68
*,». .- I
RUN 18
• >
GRUMMAN LOW SPEED WIND TUNNEL TEST NO 0210Z AXIS AXIS ANGLES FORCES MOMENTS!
ATTACK YAW
00*00
LIFT
-00*2368
DRAG SIDE PITCH YAW ROLL RUNZ t
W -04*09 00*0347' -00*0018 00i0592 00*0013 -00*0018 018Z W -01.97 00*00 -00*0599 00*0301 -00*0010 00*0344 00*0013 -00*0016 018Z W 00*14 00*00 00*1227 00*0312 -00*0014 00*0109 00*0015 -00*0015 018Z W 02*26 00*00 00*2981 C0*0364 -00*0025 -00*0119 00*0016 -00,0022 018Z ir-Ö4V39 00*00 00*4830 00*0464 -00*0020 -00*0338 00*0016 -00*0016 oiez W 06*51 00*00 00*6613 00*0393 -00*0028 -00*0545 00*0014 -00*0024 018Z Vf 08*62 00*00 00*8303 00*0774 -00*0025 -O6*0i778 00*0016 -00*0011 018Z W 10*73 00*00 00*9970 00*1018 -00*0018 -00*1056 00.0017 -00*0014 018Z W" 11.77 00*00 01*0497 00*1278 -00*0054 -00*1411 -00*0003 00*0010 018Z W 12*80 CO* 00 01*1017 00*1551 -00*0104 -00*1522 -00*0001 00*0080 oiez ff~ r3*"81 coiöib" 01*1209*" 00*1814 -00*0079 -öo*i*i1 -00*0004 00*0063 0182 W 14*84 00*00
00*00 01*1588 01*1873
00*2041 0Ö*J2Ö9
-00*0083 -00*0054
-00*1589 -00*1«13
-00.0005 -00*0003"
00*0042 0182 W 15.86 00*0036 0182 W 16*88 00*00 01*2194 00*2398 -00*0068 -00*1747 -00*0002 00*0021 0182 ((T "17*88' 00.00 01*2266 00*2717 •OO9OO46 -00*2014 00*0012 00*0028 oiez W 18*87 00*00 01*2209 00*3006 -00*0212 -00*2687 00*0038 00*0077 oiez
RUN 20
AXIS ANGLfS' ATTACK
GRUMMAN LOW SPEED WIND TUNNEL TIST NO 0»1Q2 FORCES MOMENTSZ
YAW LIFT DRAG SID€ PITCH YAW Jfikk JWtf-
.AA1S
W" W JT W sr W vr w T w tr w r
»01*97 00*14
"ÖOTÖff" 00*00
•00*2'29r •00«03»3 00*1270
00*0347 00*0301 00*031»
00*0003 00*0000
00*0424 00>0180 00*0049
00*0002 00*0003
•00*0019 'OOtOQH
0202
020Z MSI
■00*0003 02*26 00*00 00*3039 00*0368 -00*0010 -00*0258
"55757" 06*91 "sr*6r 10*73
00*00 00*00
00*4873 00*6649
00*0460 00*0607
00*0004 •00*0022
11*77 12*80
00*0007 •00*0003
•00*0461 »00*0699
00*00 00*00 00*00 00*00 00*00
00*8295 00*9934 01*0469 01.0619 OI.iHö 01*1506
"öl*17«7 01*2129 61*22)7
00*0788 00.1003
00*0000 •00*0007
«00*0351 ■00*1111
00*0004 00*0007
00*1213 -00*0003 -00*1244 00*1478 -00t0pi4 -Mttm 00*1710 00*0010 -00*1355
00*0004 00*0006
-00*0020
00*0004 QOiQ094
•00*0019
00*0002
020Z
020Z ^02 020Z
w
14*84 00*00 15*86 16*88 17*81
00*00 00*00 00*00
00*0010 00*2019 -00*0010
~0Ö*2146 00*2402 00*272*
-00*0016 »00*0028 •60*0010
•oo« •00*1619 -00*1766 •06*1832 •00*21)9
00*0001 •00*0022 -00*0023 •00|0025 -00*0007 00*0013
00*0040 00*0027 00*0016 09tOOQO
020z 020Z 020Z
J>L0Z 0202
18*87 00*00 01*2144 00*2981 -00*0137 -00*2709 00*0024
69
**
— V-'» M^r . „^_ «-
•'
AXIS ANCLES ATTACK
RUN 22
GRUMMAN LOW SPEED WIND TUNNEL TEST NO 0210Z FORCES ' " " MOMENTSZ
YAW LIFT DRAG SIDE PITCH YAW ROLL RUNZ
W W W W W W ir w W" w (T w w w r w
-04,09 -01.97 "00.14
02.26 " "54.39
06.91
10.73
00.00 00.00 00.00 00.00 OOiW 00.00
"ffö.'oö 00.00
"1T.T7 00700 12.80 00.00
TTTIT 14.84
Tr.86 16*88 17*lt' 18.87
00.00 00.00 "ooroo 00*00 00*^0 00*00
-00*2498 •00*0743 00*1169 00.2996 00*47Tr" 00*6671 ÖÖ784lT~ 01*0026 ÖT7059r~ 01.1010
'WiliO'C 01*1768
"0IT2Ö71 _0li2367_ 01*2382 01*2382
00.0350 - 00.0315 - 00.0322 - 00*0375 ■ 00*0474 - 00*0614 - OO^OTJB-- 00*1029 -
00*0025 00.0010_ 00,0021 00.0025
00.1049 JWiOTO*. 00.0342
-00*0012 00*0025 00*0028
'00*0346 •00*0701
00*0009 _00*00ll 00*0011 00.0013
00*0026 00*0032 00*0064-
•00.1052 •00.1460
00VII55 00.1508 -00*0028 - Ö3TT74T 00.2020
'00.0021 •00.0050
Öö.l6f.3" 00.1724 TSÖTüTT 00*2094
00*0012 00.0011
■oo.öoi3 oo*qpii_ 0^*0019" 00*0011
•00*0026 •00*0026_ ■00*0021 •0jp,OO23 •00*0023 •00*0016
•00*0050 00*2328 00*2403_ 00*2>i"T9 -00*0151 -00*2825 00*3003 -00*0146 -00*3212
bo.'ööTö" -00.0009 -00.0010 -00*0004
" 00*0003" 00.0009
•00*0013 •00,0026 00« 0013 00*0039 00*0046 J)0*0040 00*0027 00*0017 00.0038 00*0096
RUN 24
GRUMMAN LOW SPEED WIND TUNNEL TEST NO 021QZ Axis ANGLES FORCES MOMENTSZ
ATTACK YAW LIFT DRAG SIDE PITCH
AXIS
*
022Z 022Z 022Z 022^ 022Z 022Z 022Z 022Z 022Z 022Z
■02~2Z 022Z "0222 022Z 022Z 02?Z
JLXLS
JtÄW. ROLL .auai.
w v w
W W~
w r w r w r w
-04*09 -01.97 00*14
m 06*91
"51767
TT777 12*80
TJ7TT 14*84
16*88 17*1«
00.00 00.00
"OÜ7W
•00.2404 •00*0699 00*1220
00*0369 00*0326
•00*0007 •00*0003
6 00*00 00*30
00*00 00*48 00*6649 00*8476
00*0333 -00*0014
00*0871 00*0484
0*3010 09f9?9? -(?9t(?02i - 0*487300*0493 -00*0003 - 00*04^
00*0629 00*0811
00*0003 00*0016
00*0143 OQtQigl
00*0003 QOtOOOl
10*73 00*00 01*0064 00*1040 00*00 00*00
■55^5" 00*00
"ÜO^ÖÜ" 00*00 00*00
01.0977 Ms
•00*0025 •00*0007
•00*0492 •00*0777
00*0004
QQtQQOl
•00*0021 -00*0021
•00*1131 'O0t193?
00*0003 00*0004
•00*0021 ■0fliQQ24
00*0004 00*0002
•00*0027 -00« 0020 •00*0016 '00*0017
00*1242 -00*0010 -00*1674 00*0007 00*0013 00*1929 -00*0010 -00*1794 00.0005 00.0033 00*1799 -00*0003 -00*188100*000000*0042
01*1949 00*1960 00*0007 -00*2019 00*0000 00*0039 »
01*2194 01*2317
"ör*2fjr •00*0014 18*87 00*00 01*2447 00*3043 -00*0036
00*2180 00*2406 00*2735"
00*0000 •00*0014
•00*2203 •00*2398 •00*2720 •00*3091
•00*0012 •00*0029 •00*0006 00»0007
00*0020 .oosOOJLL 00*0019
024Z AZkZ 024Z
J>2&Z :42
024Z 024Z 024Z 0242 024Z
024Z
024Z
70 t:'
i-t,.,"^r">
_
RUN 26
AXIS ANGLES ATTACK
GRUMMAN LOW FORCES
YAW LIFT
SPEED WIND TUNNEL TEST__NO 0i±0Z MOMENTS!
DRAG S^DE PITCH
AXIS
1AM ROLL jmi
w w w w w w w w vr w
-04.09 _00.1_5 02.27 04.39 06.51 08.62 '10.73 11.76 12.7? 13.83
« r4.86~ W 15.88 W 16.B7 W 17.88 W 18.91
00.00 _00.00
o'b.ob" _00.00
00.00 00.00 '00.00 00.00 Ü^.OO 00.00
inr.w 00.00 00.00 C0.00 00.00
•00.2360 00.1249 00.3075 00.4952. 00.6736 00.8425 01.0129 01.0541 01.0996 01.1487 01.1804 01.2035 01.2180 01.2281 01.2996
00.0365 00.0341 00.0401
J)0.049J_ 00.0640 00.0817 00.1064 00.1301 "00.1564 00^1812
00*2262 00.'2 5 ST 00.2787 00.3188
00.0014 -00.0010, -00.0010 -00.0018 -00.0007 -00.0025_ -ÖÖ.00Ö3 -00.0021 -00.0751^" 00.0010
00*0930 _0Ät03_05_
•00.0022 ■00.0322
y0'.0003 00.0014 ÖÖ»ÖÖÖ7
-00.0003 -00.0205
•00.0609 ^00.0945 •00*i3T8 •00.1507 •00.1563 •00.1698
00*0005 00.0005 60*0006 00.0010
•ÖÖ*l8^ • •00*1985 - •öö«2231 •0012470 _• ;00.3568 «
00*0009 00*0008 "ö'ö7ööör9" 00*0013
TJOTOOOr 00*0002
•00*0018 •00.0017 •00.0023 •00.0020 •00.0017 L00_*0018 •00.0021 00.0022
00*0009 •00*0017 00.0502 00*0001 •00*0042
00*0039 00*0033 00*0023_ 00.0026 00*0038 ■00»0287
026Z .Q26Z 026Z OJftZ n?6Z G26Z 0,'6Z 025.Z 026Z 026Z 026Z 026Z 026Z 026Z 0?6Z
RUN 28
AXIS ANGLES ATTACK
GRUMMAN WOW SPIED FORCES
YAW LIFT
WLNfi-jmNEL TESI-Üg 0210Z_ MOMENTSZ
fifiAG 5iߣ PITCU YAW ROLL
AXIS
BUNZ
W W W w vT w W" w_ w w
•04**0 •04.08 -Öl.97
04.39 "56.Tr 08.62
"ÖÜTÖO 00.00
TOffO
•00.3133 •00*1573 •00 .'0507"
00.15 00*00 00*1660
00.00 00*3*41 00*4887 00.6461 00.8006 '00.'9*44 3
00*0318 00*027» 00*0253' 00*0277
•00*0003 lfl.0*0SL2.L •00*0010 •00.0036
•00*1109 •-QQ-tQ949 •00*0777
00*0015 OQiQQlfe 00*0016
•00*0020 .QQ.QOli •00*0018 ■OQiOQM
028Z J12AZ 028Z
AMI
10.73
13.83
00.00 00.00 00.00 00.00
00*0336 00*0439 00.0573 00*0739 00.0946
OOtll»
•00.0016 •00.0021 •00.0039 ■00.0039
•00*0431 •00*0257
•00.0021 'QQiOQH
•00*0084 00*0085
00*0017 00.0017
00*0208 QQtOl»
00*0018 Q0t0019
•00*0021
00*0021 Q0i0Q24
•00*0017 •QOiQQIB •00*0019 QQtQQIS
028Z .Q28Z 028Z .029 Z 0281 028Z
W w W' w
14*66 15*86
00.00 00.00 0Ü7ÜÖ"
01.0266 01*0793 "ÖI.1147
00*1423 00*1646
•00*0036 •00*0023
00*0119 00*0125
00*0023 00*0019
00*0042 9Pf093?
028Z ^281 028Z
_0181 026Z Mil w
vT
00.00 01*1414 00*1629 00*1991
•00*0018 •00*0014
00*0125 00*0156
00*0019 00*0016
00*0039 00*00??
16.67 17.66 16.91 19.92
0Ö7Ö0 00.00
01*1292 01*1429 01*1676 01*2006
00*2391 00*2613
•00*0029 •00*0003
•00*0007 •00*0005
00*0017 00*0026 oo»oo»o
00*00 00*00
00*3007 00*3221
00*0321 00*0332
•00*0449 •00*0499
•00*0097 •QQtOO?4
•00*0199 ■Q0tQ»4
0262 Q2M
71
RUN SO
GRUMMAN LOW SPEED WIND TUNNEL TEST NO 0210Z AXIS AXIS ANGLES FORCES M0MENTS2 "
^ATTACK YAW LIFT DRAG SIDE PITCH YAW ROLL RUNZ *
W -06.19 00.00 -00.3082 00.0253 -00.0018 -00.1121 00.0016 -00.0018 030Z w -04.08 00.00 -00.1523 00.0209 -00.0014 -00.0979 00.0016 -00.0014 030Z w -01.97 00.00 00.0000 00.0191 -00.0014 -00.0850 00.0016 -00.0023 0302 w 00.15 00.00 00.1617 00.0209 -00.0032 -00.0718 00.0017 -00.0022 Ü30Z • w 02.26 00.00 00.3184 00.0263 -00.003? -00.0577 00.0019 -00.0023 030Z w 04.39 00.00 00.4851 00.0155 -00.00?8 -00.0439 00.0019 -00.0024 030Z w 06.50 00.00 00.6433 00.0472 -00.0043 -00.0304 00.0020 -00.0019 030Z w 08.62 00.00 00.7985 00.0620 -00,0043 -00.0148 00.0018 -00.0018 030Z ) w 10.73 00.00 00.9501 00.0803 -00.0025 00.0006 00.0020 -00.0022 030Z w 11.78 00.00 01.0172
01.0887 CO.0913 00.1011
-00.0032 -00.0032
00.0084 "00.0176"
00.0019 00.0017
-00.0014 -00.0011
030Z Ö30Z w ' IT. 84 Uo.bo
w 13.88 00.00 01.1515 00.1133 -00.0036 00.0251 00.0019 -00.0011 030Z w 14.92 00.00 01.2035 00.1245 -00.0032 00.0321 00.0019 -00.0009 030Z | w 15.93 00.00 01.2129 00.1386 -00.0010 00.0246 00.0007 00.0009 0302 . w 16.93 00.00 01.2122 00.1766 00.0068 -00.0058 -00.0018 00.0079 030Z 1
-
AXIS ANGLES ATTACK
RUN 32
GRUMMAN LOW SPEED WIND TUNNEL TEST NO 0210Z FORCES MOMENTSZ
YAW, „WlfjL. . DRAG SIDE PITCH YAW . .ROLL „ .RUNZ.
AXIS
W w W" w W" w
w w
W -06.20 00.00 -00.3133 00.0228 W -Öl* 14 00.00 -flQ. 2339__0!1AW09 W -04.08 00.00 -00.1581 00.0191 W -03.03 00.00 -00.0808 00.0180
•01.97 •00.91 00.14 01.20 02.26 03*32
00.00 00.00
"50.00 00.00_
"ÜÖ7Ö0 00.00
-00.0010 -00.1148 00.0016 -00.0007 ■--Jaj.afl03-rfl0>10fl4 aQ*ilQl6_H00*0O06. -00.0010 -00.1020 00.0016 -00.0010 -QO.QQfl? -00.0957 nn.ftni& -nn.nni4
•00.0021 00.0173 -00.0018 -00.0891 00.0772 00.0177 -00.0010 -00.0817 00.1588 00.0190 -00.0025 -00.0747 00>240» 00_.02.12 -00.0021 -00.0685 00.3198 00.0246 -00.0021 -00.0622 00.3999 00.0288 -00.0025 -00.0551
00.0018 -00.0011 00.0018 -00.0013 00.0018 -00.0015 00.0018 -00.0015 00.0018 -00.0012 00.0018 -00.0010
10.73 11.79 12.83
032Z -032Z 032Z
— 032Z 032Z
._032Z 032Z 032Z 032Z
...Ä322 W 04.39 00.00 00.4837 00.0337 -00.0025 -00.0474 00.0019 -00.0009 032Z W 05.45 00.00 00.5646 00.0395 -00.0025 -00.0402 00.0019 -00.0009 032Z W 06.50 00.00 00.6360 00.0459-00.0028-00.0331 00.0018-00.6012 0322 W_ 07.56 00.00 QP.7205 00.0531 -00.0028 -00.0254 00.0018 -00.0010 Q32Z
-W "08.62 00.00 00.7985 00.0605-00.0021-00.0174 00.0020-00.0012 032Z W 09.68 00.00 00.8728 00.0698 -00.0025 -00.0101 00.0019 -00.0013 0322
00.00 00*.9508 00.0792 -00.0028 -00.0025 00.0018 -00.0015 032Z 00.00 01.0252 00.0901 -00.0018 00.0058 00.0017 -00.0008 _032Z 00.00 01.0830 00.1005 -00.0021 00.0132 00.0016 -00.0009 032Z
I
72
k- , r
RUN 39
AXIS ANGLES ATTACK
GRUMMAN LOW SPEED WIND TUNNEL TEST NO 02102 FORCES MOMENTS!
YAW LIFT DRAG SIDE PITCH YAW ROLL RUNZ
AXIS
W -Ö4,0f 00*00 •00*2*13 W 00.1» 00*00 00*11*2 « Or.27 00.00 00.2989 W 0**S9 00.00 00**t22 r—w.n—öO*^ö- ^o***«2 W 08**2 00*00 00*8*9* w— nvn—w.oooi.on» W 11*7* 00*00 01*0671 W TZTTT~ 00**0 01 * OS»* W 13*89 00.00 01*1*07 i—IF*T*—onj.ao ~^i iinr W 19*88 00*00 01*2299 W TFiTT—00.00 01.2*92 W 17*88 00*00 01*2996 W IWiVl —00*00 01 • 9198
00*0968 -00*0007 00*0882' 00*0012 -00*0008 0392 00.09*0 -00*0021 00*02*9 00*0011-00*0019 0392 00.0399 -00.0021 -00.00*9 00.0019 -00*0026 0392 00.0*99 -00*0029 -00*0990 00*0011 -00*0029 099Z 00*0692 -00*001* -00*06*2 ~~00*00'i9 -00*0020 0992 00.0810 -00.0007 -00.0990 00*0012 -00*001* 0992 00*109* -00*0018 -00.1980 00.0019-00.001* 0992 00.1291 00*0021 -00*1976 -00*0006 -00*00*0 0992 00*1960 -00.0007 -00.1986 00*0011 00*0012 0992 00.1769 00.0007 -00*16*9 00*0007 00*0027 0992 00.1966 "00.0010"=00.lTT«~~0ö*"ÖÖÖ6'~50*OO9* "~T)99Z 00.2166 00*0009 -00*1900 00*0008 00*0090 099Z 00.2*61 00*0010 -00.2198 00*0092 00*00*9 0992 00.279* 00.0018 -00.2*19 00*000* 00*00** 0992 00.3193 00*0169 -00.3909 00.0022 -00*0202 0992
RUN 41
AUS mscar ATTACK
GRUMMAN LOW SPEED WIND TUNNEL TEST NO 01102 FORCES M0MENU2
YAW LIFT DRAG SIDI PITCM YAW
AXIS
J9U. KUftt »
r w r w r
w r r w r
00*19
9M? 08*62
11*76
19*89
19*68
17*88 11*91
00*90 00*00 00*00 00*00
00*00
00*00 00.00 00*00
•00*2*69 00*1176
'00*9099 U*87 s::n? m
W64618.91
00*00 "W700_
00.00 "W*"00" 0«*00
00*8977 61 «Olio' 01*1099 ~ör*yw 01*2119
00*0968 00.0397 00*0390
*99
oi*mf 01*2981 «T?T*9 01*9068
01*2992
69« 00*081» 00*10*T 00*1199
00*1699
00.2281 ÖÖ.2699 00*9010 oo*f9*r 00*39*9
-00*0021 —OOfO092_ -00*0029
-00*0028 -00*0028 -00*0021 -00.0018 -00*0018 -00*0096.
00*0000 -00*0029 -00*0021 -00*0090 ~oo*oiör SYY*0101
00*0809 00*001* -00*0019 06#02|l_.M*O0l* ^•0029
-00*0071 00*0019 -00*0018
-00*06*6 *0990
-00.1999 -00*1611 -00*T8*r -00*1976 -00*21*9 -00*2989
"=050517 -00«2772 -o^*9*ir -00*T*98
00*0019 00*f<)12 00*001!
-00*001« oo*o«ro 00«0»2^ 00*0003
-00*0029
-et*oo2e ^»»0021 -«••0021 -00*0019 "SO*ÖÖ59"
fo«»0*». w*0O** 00*0097
>00*00** 'J0iM|2 •00*0099
U0201 ^OJM »•0***
0*12 JL*iZ 0*1Z
JUkll 0*1Z
-&41Z 0*1Z
_0*l» 0*1Z
-00*0009 -00*0*YU
0*1Z _0*1J 0*1Z
^*11 0*1Z o*iz
73
r*
■
. ^.i** r*rS3* - * „.-^-^^ *-■*■ *
APPENDIX II RAW DATA
RUN
007
A ANGLE LIFT
ÜÜ7— 007 007" 007 007" 007
007
49940 —«99»0
49980 "10000
50020 —50040
50060 "50080 50100
IT 50140
■JOIIO" 50180 2üD~
50000 50000 50000
"50000 50000
~?0000 50000 "sooao 50002 50000 50000 -1ÜÜ02 50000 -50Ü02-
DRAG
49999 50000 49999 49999 49999 49999 50000 50000 49999 50000 49999 49999 49999 49999
PITCH
49948 49972 49987 50001 50009 50014 50016 50013 50006 49992 49978 49955" 49933 49904
YAW
50000 50000"^ 50000 50000 50000 50000 49999 49799 49998
—4999r 50000
"SOOOO" 49999
• 49999"
ROLL
50000
50002 50003 50002
~5O0O3 50003
"50001 50003 "50003 50004
SIDE Y ANGLF
50000 0""
50000 50000" 50000
50001- 50003 5UUU4
50U00 50000 TÜO0Ö" 50000 50Ü00
50000 T^OOO
50000 -^^ooo 50000
"100 00 50000
00 50000
■5ÜÖO0 50000
TOOOO 50000 50UUÜ
RUN
008 -oor 008
008
008 TOT 008 oor 008 -oor 008
-our 008 -oor
A ANGLE LIFT DRAG
50131 101 ij-
PITCH YAW
49940 49156 -17TOJ—vwm
49980 50044 50104 ■"3000a 50*92 5OI0T-
50020 50960 50113 "50130"
50060 51882 50156
ROLL SIDE Y ANGLE
49557 50027 "^9 513 7ÜÜ7B
50006 50003
49705 "49770
49830 "47883'
50030 Tcroiö- 50033 50015_
"5Ü01D■ 50100 50110 50120
50140
52830 52724 52916- 53060
53226
5P194 50239
"50269 50329
"50417- 50472
■50530" 50627
"50587
49929 50036 -5TO7 5BffW
49992 50040 "4999T 5004r
49962 50031 "49970 5TJ046- 49900 50053
50000
49997 50002 50000 -vmn—nwpi—"5OöüO 50003 49996 50000 '50ÖÖÖ 49799 n 0 ÖÖT 50003 49999 50000 50000 49996 50012 50023
5U19U 50160 50170
53190 53220
49899 50043 49860 50022 478H 500T4
"SOTOr 50252 500/2 50095 50112
49995 SOÖÖÖ 49797 50000
"5ÜÜÜ0 5ÜOÜ0" 50004 50000
"47955 50000 49947 50000 49963 ITODTT 50000 50000
"49992 50000"
74
-—-
RUN A ANGLE LIFT DRAG PITCH YAW ROLL SIDE Y ANGLP
009 49940 49148 50133 49555 50022 50007 49999 50000 009 49960 49590 50115 49631 50021 50005 50000 50000 009 49980 50034 50106 49703 50023 50004 49998 50000 009 50000 50482 50106 49766 50024 50004 49998 50000 009 50020 50952 50113 49824 50025 50000 49996 50000 009 50040 51408 50133 49882 50029 50006 49999 50000 009 50060 51852 50159 49928 50028 50007 49998 50000 009 50080 52278 50196 49960 50030 50000 49994 50000 009 50100 52708 50244 49980 50036 49997 49995 50000 009 50110 52900 50276 49974 50027 49988 49999 50000 009 50120 52950 50366 49939 50018 50071 50001 50000 009 50130 53062 50418 49931 50017 50079 49999 50000 009 50140 53132 50463 49928 50018 50085 50001 500CO 009 " 50150 53148 50532 49901 50020 50039 ~49982" ■ 50000' 009 50160 53252 50588 49885 50026 50022 49976 50000 009 50170 53218 50664 49858 50024 50039 49989 50000 009 50180 53158 50748 49751 50059 50061 49951 50000
RUN A ANGLE LIFT DRAG PITCH YAW ROLL SIDE Y ANGLE
014 -014 014 014 014 014 014 "OTT 014 -air 014 "OTT 014 ■orr
49940 49960 49980 50000 50020 50040 50060
■"5Ü080 50100 50120 50140 90160 50180
■50200'
50000 50000 50000 50000 50000 50000 50000 50000 50000 50000 50000 50000 50000 90000
49999 50000 49999 49999 50000 90000 50000 49999 49999 90000 49999 49999 49999 90000
49948 49969 49987 49999 50009 50011 90012 50011 50000 49990 49972 49951 49«23 49897
50000 50000 50000 50000 50000 50000 50000 50000 50000 50000 50000 50000 50000 SOtJOO-
50001 50001 50001 50001 50002 50002 50002 50002 50002 50003 50003 50003 50004
'■~90TJ04
50001 50001 50002 50001 50001 50001 50001 50001 50001 50001 50001 50001 50001 50001
50000 50000 50000 50000 50000 50000 50000 50000 50000 50000 50000 50000 50000 50000
75
\
:.t
—■v;-»'
PUN A ANGLE LIFT DRAG PITCH YAW ROLL SIDE Y ANGLE
015 49940 49136 50121 49558 50020 49973 49998 50000 015 49960 49558 50103 49624 5002? 49980 49993 50000 015 49980 49994 50094 49681 50023 49972 49998 50000 015 50000 50436 50092 49734 50023 49982 49995 50000 015 50020 40880 50098 49779 500?4 49975 49995 50000 ni5 50040 51336 snn? 498?? 5no?6 49982 49997 50000 015 50060 51784 50136 49857 50026 49970 49991 50000 015 50080 52210 50165 49887 500?6 49976 49994 50000 015 50100 52634 50203 49912 50026 49972 49991 50000 015 50110 52826 50222 49925 50026 49976 49992 50000 015 50120 53014 50246 49937 50026 49977 49993 50000 015 50130 53190 50266 49949 50027 49991 49994 50000 015 50140 53344 50292 49961 50020 49989 49993 50000 015 50150 53460 50317 49964 500?1 50004 49997 50000 01^ 40160 43348 50405 49844 49951 50135 50037 50000 015 50170 53426 50464 49802 49957 50167 50033 50000
I
RUN A ANGLE LIFT DRAG PITCH YAW ROLL SIDE Y ANGLF
016 49940 49116 50142 49560 50022 49969 49997 50000 Old - 49960 49552 50124 49636 50023 49963 49995 50000 016 49980 49986 50113 49706 50023 49960 49996 50000 016 90000 50^38 50113 49770 50024 49958 49994 50000 016 50020 50878 50121 49830 50025 49958 49993 50000 016 50040 51348 50138 49882 50026 49972 49994 50000 016 50060 51796 50161 49928 50028 49963 49993 50000 on — 50(T80~ 52224 50196 49967 ~ 9002ff" ' "49966 " 49995 50000 016 50100 52630 50240 49988 50034 49978 49994 50000 016 - 50110 52778 50284 ' 49976 - 50037 50034" 49991 • 50000 016 50120 52866 50347 49953 50033 50065 49988 50000 016 50130" 52920 50440 49909 50011" -50103 " -49975 " 50000 016 50140 53016 50497 49895 50008 50092 49976 50000
■016- " - 50130" ' -53096 50540 49889 5Ö0Ö4 ■ -SOOS* "59972 50000' 016 50160 53170 50587 49880 50015 50040 49969 50000 -ott— - 50170 53200 50641 49893 50031 50035" 49996 50000 016 50180 53152 50739
50807 49752 49713
50061 JT W W *1 Ü"
50083 50070 "
49942 -50045
50000 -50000 016 50190 " 53100 49V30
•
76
t • ■ '.V
Ji —
RUN A ANGLE LIFT mur* PITCH VAW "DLL MOF V AMGL^
017 49940 50000 49999 4994^ sooo? 49998 =•000?. 5O0C/C 017 49960 50000 49999 4Q9f6 50002 4999P = 0001 50000 017 49980 50002 49999 49986 5000? 49998 ?0001 50000 017 50000 50000 49999 49999 49999 4999« R0001 50000 017 50020 50000 49999 50010 50000 49998 50001 50000 017 50040 50000 49999 50016 50000 49998 50001 50000 017 50060 50002 500O0 50016 50002 49998 50001 50000 017 50080 50000 50000 50014 50001 49998 50001 500CC 017 50100 50000 50000 50007 50001 49999 50001 50000 017 50120 50000 49999 49Q96 50001 49999 50001 50000 017 50140 50002 50000 49y77 50002 49999 50001 50000 017 50160 50000 50000 49957 50001 49999 50001 50000 017 50180 50000 50000 49931 50002 49999 50001 50000 017 50200 50000 50000 49901 50002 49999 •iOOOl 50000
RUN A ANGLE LIFT ORAG PITCH YAW ROLL SIDE Y ANGLE
018 49940 48856 50170 50250 50026 49962 49996 50000 018 " 49960 49344 50145 50174 50024 49966 49996 50000 018 49980 49836 50128 50106 50025 49970 49998 90000 018 50000 50340 50124 50031 50025 49971 49997 90000 016 50020 50826 50130 49954 50028 49959 49994 90000 018 50040 51338 50147 49871 50028 49969 49993 50000 018 50060 51834 50173 49783 50026 49957 49993 90000 oit — 50080 52300 50212 49683 50028 49978 49994 " 50000 018 50100 52762 50268 49562 50030 49974 49996 90000 018 " 50110 52908 50331 49436 49996 50014 49986 50000 018 50120 53052 50402 49391 50000 50129 49972 90000 018- 50130 53106 50472 49379 49995 50102 49979 50000 018 50140 53212 50531 49344 49993 50067 49978 50000 018 - 90150 53290 50575 49313 49993 -5005B -49986 50000 018 50160 53378 50625 49260 49997 50033 49982 90000 OW 90170 53398 50712 49162 50022- 50044 49988 50000 018 50180 53382 50793 48939 50068 50121 49942 90000 ott— 90190 53376 50864 48857 49934 -50072- 50093 ~50000
77
.
V
RUN A ANGLE LIFT DRAG PITCH YAW ROLL SIDE Y ANGLE
f)19 49940 50000 50000 49941 50001 50000 50000 50000 019 49960 50000 50000 49967 5000? 50000 50000 50000 019 499B0 50000 50000 49984 50000 50000 50000 50000 019 «0000 50000 50000 4999'» 50000 50000 5Ö000 50000 019 •00?0 50000 50000 50008 50000 50000 50000 50000 01«? 50040 50000 50000 50014 50000 50000 50000 50000 019 50060 50000 50000 50017 50000 50000 50000 50000 019 50080 50000 50000 50014 50000 50000 50000 50000 019 50100 50000 50000 50006 50000 50001 50000 50000 019 50120 50000 49999 49995 50000 50002 50000 50000 019 50140 50000 50000 49978 50000 50003 50000 50000 019 50160 50000 49999 49957 50000 50003 50000 50000 019 50180 50000 50000 49931 50000 50003 50000 50000 019 50200 50000 50000 49901 50000 50003 50000 5 0000
i
•
RUN A ANGLE LIFT DRAG PITCH YAW ROLL SIDE Y ANGL
020 49940 48886 50170 50186 50006 49958 49999 50000 020 49960 49364 50146 50121 50006 49968 "50001 50000 020 49980 49846 50131 50051 50006 49962 50000 50000 020 50000 50352 50126 49980 50008 49962 - 49999 50000 020 50020 50842 50132 49907 50006 49957 49997 50000 020 50040 51350 50147 49829 50007 49967 50002 50000 020 50060 51842 50177 49749 50013 49963 49999 50000 020 50080 52298 50216 49660 50007 •49937" "~5Ü00Ö " 50000 020 50100 52752 50264 49543 50010 49963 49998 50000 020 50110 52900 50313 49487 50008 50006 49999 50000 020 50120 52996 50382 49466 50007 50065 49996 50000 020 50130 53136 50443 49430 50002 50083 50003" "50000 020 50140 53188 50525 49337 49963 50048 49997 50000 020 - - 50150 53268 50571 49292 ■49961" ' 50Ö34- ■ «997 ~BO00O 020 50160 53360 50625 49233 49958 50012 49992 50000 020 50170 53390 50714 49122 49988 50043" ~ 4999r 507)00 020 50180 53364 50786 48929 50024 50083 49962 50000 020 50190 53390 50851 48833 50039 50107 - 49954 50000
.■
■
78
RUN A ANGLE LIFT DRAG PITCH YAW ROLL SIDF Y ANGLE
021 49940 50000 50000 49939 50000 50001 50001 50000 -on— - 49960 50000 50001 49964 50000 50001 50001 50000 021 49980 50000 50000 49964 49999 50001 50001 50000 V7r~ 50000 50000 50000 49999 49999 50001 5000^ 50000 021 50020 50000
50000 50000 50000
50009 50017
49999 50000
50000 50000
50002 50002
50000 un 50040" 50000 021 50060 50000 50000 50019 50000 50000 5000? 50000 VTl 5tJÜ80 50000 50000 50015 49999 50000"- 50002 50000 021 50100 50000 50000 50005 50000 50000 50002 50000 ü2r- - 50120 50000 49999 49995 49999 50000 50002 50000 021 50140 50000
50000 50000 50000
49979 49957
49999 49998
50000 50000
50002 50002
50000 ~02T "Jtn 60 50000 021 50180 50000 49999 49932 49999 50000 50002 50000 ÜTT ' ■50200 50000 50000 49901 49998 50000 50002 '50000
RUN
022
022 022- 022 -Ott 022
A ANGLE LIFT
■022— 022
~022 022
-022— 022
49940 50
49980 50000 50020
"50040 50060 30080 50100
0 50120 50130 50140
TTTT 022
-022 022
■50150' 50160
-3O1T0- 50180
48812 49308 49794 50324 50830
—51322 51648
52350' 52778 92934 53050 531ir8 53260 5T5V4
53426 "55430 53430
DRAG
50175 50148 50133 50126 50134 50151 50179 -50215 50270 50319 50390 5045? 50525 50572 50626 50701 50791
PITCH
50431 50320 50221 50107 49988 49870 49736 •49 597- 49429 49354 49323 49276 49180 49130 ' 49070 48897 48764
ROLL SIDE Y ANGLE YAW
50014 49953 49997 50000 50015 47751 49994- 50000 50018 49956 49998 50000 50018 49965 49997_-50000 50022 49960 49995 50000 50020 49960" 49995 «0000 50019 49972 49994 50000
-50022 49975 49V94 5Ü0 00 50020 49955 49993 50000
_50O33 50037" 47984 50000^ 50019 50065 49994 50000 50016" 50077 47976" "70000 49984 5006649988 50000
—49787 50045 59791 50000" 49991 50028 49988 50000 50006 50057 47960 "50000 50017 50086 49961 90000
79
.'.<
.
RUN A ANGLE LIFT DRAG PITCH YAW ROLL SIDE Y ANGLE
023 49940 50000 49999 49939 50001 50002 50001 50000 -W3 - -»9960 50000 50000 49965 sooor —50007"" 50001 "50000 023 49980 50000 49999 49984 50002 50002 50001 50000 -023 50000 50000 49999 49999 50000 50007 —50ÜÖ1 " 90000 023 50020 50000 49999 50011 50000 50002 50001 50000 ~02r 50040 50000 49999 50015 50000" 50002 50001 50000 023 50060 50000 49999 50017 50000 50002 50001 50000 023 JOOTO ~50OO0 49999 50014 • 50000"" 5UÜU2 90001 - 50000 023 50100 50000 50000 50009 49999 50003 50001 50000 -02»~ 90t20 90000 49999 49996 49999 50003 5ooor 50000 023 50140 50000 49999 49979 49999 50003 50001 50000 0» 90160 50000 50000 49958 49999 50003 50001 50000 023 50180 50000 49999 49933 49999 50003 50001 50000 -073— -502U0 • 90000 49999 49902 49999 50005 50001 -•50000
RUN
024
02«» -07«r
A ANGLE LIFT
024
024 -07*- 024
024 -OW 024 -02«- 024 -07*- 024
49940 "*^»tr 49980 -500OO 50020
"90040— 50060
48832 49T34 49824 50338 50834
-91390^ 51842
50080 52348 50100
-—9ono— 50120 30130 50140
52788 -57930 53056
"95X58 53310
DRAG
50175 50151 50135 50130 50138 50195 50182
■50221
80190—nrn 50160
-90170— 50180
53412 ■53404 53448
50274 "90321
50396 - 50455
50507 50966
50627 —-50715
50802
PITCH
50359 50264 50150 50043 49936 49821 49710 49969- 49410 49350 49315 4926i 49202
—49176 49049 -45939 48805
YAW
49999 50O08 50004
"50005 50003 "50005" 50007
-5DÜÜ8 50003 -90011- 50008 -49998- 49998 4VV7V 49956
■49989 50011
R9,rL_ SIDE Y ANGLE
49959 50000 90000
49967 50000 50000 49969 49797" ■ 5^00 49960 4999550000 49957 "50000 50000 49968 49996 90000 49V/4 59995 5WD00 49973 49999 öOOOO
"50025 ^9998 50000 50059 49998 50000' 50074 50000 50000" 50068 50003 50037 50022 49997
"~90078 49997 50050 49991
90000 TOO
90000 "50000 50000
80
I
RUN
025 025" 025 025 025 025 025 V2* 025 02f- 025 025 025 •023"
A ANGLE LIFT
49940 —49960" 49980 30000 50020 50040 " 50060 50OB0 50100 50120 50140 50160 50180
"90200 "
50000 SOOOZ 50000 50000 50000 5000O 90000 90000 50000 90000 90000 90000 50000 90000-
DRAG
50000 50O0O 50000 50000 49999 500OO 50000 5000 50000 5000O 50000 50000 50000 '90000
PITCH
49939 49966 49986 50002 50014 50020 50022
50015 50002 49987 49968 49943 49912
YAW
50000 "90000 50000 50C 50000 90000 50000
ROLL
50000 "SOTJÜD" 50000
SIDE V ANGLE
49999 49999" 49999 ^9999 49999 -4T9V9-
90000 5UUUU 50000 5ÜUUÜ
50000 50000 50000 90000 50000 50000 5UUU1 50000"
50000
90000 90000
50002
50002 50002 50002 50002
50000 5UU0U
50000 -T0OUD 50000
"TOO 00 50000
"50000 50000
"50000 50000
-90000 50000
--90000 50000
-50000-
RUN
026 ■02r 026 -02«- 026
026
026
026
A ANGLE LIFT
49940 4V96Ü 49980 90000" 50020
■90040" 50060 "90080" 50100 -sotto— 50120
48844 4V34T- 49830
—90346- 50852
~9T9T2 91866 52334
DRAG
50175 -90151- 50136
-90139- 50140 9ai9T 50186
PITCH
50382 -50284' 50192 50093" 49990
- 49B81 49770
YAW_
50010 50009
ROLL
49978 4V970
SIDE Y ANGLr
4)996 50004
50006 49973 50002 -90009 Wim 49V97 50011 «9960 49997 90017 - "49969 59995" 50015 49970 49998
•70225 50281 )399
50407 90470 50539 50911 50670 -90792" " 50839
■49638 49467 49414- 49385 49927 49260 492ÜT- 49121 49029" 48699
70015 50015 50022 50014 '90003 49983
»VV69 49966 90099" 50060 50068 50058
T999r 49999 "49994 49997
03 50001
50000 -scrooo
50000 -5ÜÜO0
50000 «TTOO 50000
"TTOOÖ 50000
■"90000 50000
' 9O000 50000
"TO0ÖO 90000 9000C 90000
026" 026 -air 026 -02r 026
90130 50140 9U190 50160 90170 90180
92806
93046 93182 "■ 93270
T3334" 93374 99402- 93600
4VV70 50003 49997 49930
90052 50046 900 50472
■5Ü0U5" 90002
49943
;- ■ 1
«i nk
81
RUN A ANGLE LIFT DRAG PITCH YAW ROLL SIDE Y ANGLE
027 499*0 90000 90000 49948 50000 50001 50000 50000 orr— — 49960 90000 49999 49970 50000 50001 90000 50000 027 49960 90002 50000 49986 50000 50001 50000 50000 027 90000 90000 90000 90002 90000 90001 50000 90000 027 50020 90002 90000 90009 90001 90001 50000 90000 027 90040 90000 90000 90019 90001 90002 50000 90000 027 90060 90000 90000 90016 90001 90002 50000 90000 err - - - 90080^ 90000 49999 90012 90000 90002 50000 90000 027 90100 90000 90000 50006 50000 90002 50000 90000 027 "- 90120 90000 90000 49994 90000 90002 5 00 00 90000 027 90140 90000 90000 49978 50000 90002 50001 90000 027 90160 50000 90001 49960 50000 900J0 50001 90000 027 90180 90000 90000 49035 50000 90000 50001 90000 027 90200 90000 90000 49907 50000 90000 50001 90000
RUN
028 TJ79- 028 028 028 tJ28 028
A ANGLE LIFT
49940 -^9960 49980 9000O 50020 50040- 50060
49132 4956* 50000 50460 50900
-Sr354 51790
028 -028- 028 028 028 028 028
'9D08Ü 50100
-50110' 90120
90140 -9UI9Ü- 90160
577T8 52616 52730 52844 52990 53088
"53162 53128
-53166- 53290 T3326-
DRAG
90142 50124 50115 50115 50123 50141 50168
-50202- 50249 90307 50369 30429 90471
•90914- 90626 5068T 90790 50848"
PITCH
49564 -49667
49743 49812 49876 49934 49984
-50075- 90049 90024 50004 49995 49963
—499*0- 49926
-49913" 49759 49727
YAW
50026 50028" 50027 50028 50030 50030- 50032 50032- 50035 50041 50039 50033" 50032
ROLL SIDE Y ANGLE
50031 90029
-50020" 49901 4?9i
4996749999 "59975 £9974
49970 49997 - 49955 49990
49969 49995 -499160 ~ «994
49971 49989 49970 5992^— 49969 49994
—50055 49987 50071 49990
-50O6r- 49994 50067 49996 9UU6U —59997" 90046 49994
"50050 50ÖO0 496(6 50090 -V9yc9' " 50093
50000 50000 50000 50000 50000 50000 50000 'BOOOü 50000 30000 50000 50000 90000
—30000 90000
—5OOOO 90000 50000
,
82
- I
RUN A ANGLE LIFT DRAG PITCH YAW ROLL SIDE Y ANGLE
\
029 49940 50000 50000 49951 49998 50002 50000 50000 U79 -—• 49960 50000 500O0 49969 49999 30007" —500-00 50000 029 499B0 50000 50000 49987 49999 50002 50000 50000 029 50000 50000 50000 50002 49999 50002 50000 " 50000 029 50020 50000 50000 50009 49998 50002 50Ü00 50000 027 " —50040 50000 49999 50014 49998 50007^ —49999 50000 029 50060 50000
"50000 50000 50000
50017 500T2
49996 •4-9999 -
50002 50000 50002 50000-
50000 029 "■"5OO80 '" "30000 029 50100 50000 50000 50006 49998 50002 50001 50000 029 -50120- "50000 50000 49992 49998- 500O2 50001 "50000 029 50140 50000 50000 49977 49998 50002 50001 50000 tJ29 50160 "50000 50000 49955 *999T - "50002 ■ 50001 50000 029 50180 50000 49999 49933 49998 50002 50003 50000 VZ9 50700" - 50000- 50000 49904 49997- 50001 -5OOOT -5OOOO
RUN
030 "030" 030 030 030 030 030 "030-
A ANGLE LIFT DRAG PITCH
030 "030 030
030 -ow 030
49940 4Vy60- 49980
-50000 50020 500 40 50060 5UU8U 50100
-50110- 50120
--90130- 50140 9Ui8U 50160
49146 "«95T8"
50000 504-48- 50882 51344 51782 52212 52632
-52515- 53016
" 53190 " 53334
-53350 93358
50124 49581 -5010T--49652
50098 49716 50095 49775 50103 49826
"50117 4987r- 50140 49910 501/Ü 59945~ 50209 49976 50230 4r»8T 50250 50001 302TT 90010" 50302 50017
'903VTJ *9978 50445 49874
YAW
50026 50027 50027
5ÖÖ7B~ 50031
—5Ö030— 50032
"T0Ö3Ö 50032 50030 50027 50030 50031
^5ÜC 49966
ROLL
49971 vim 49963
-4996«- 49962
"49V60 49968 4VV69 49964 49977- 49982 "«9982 ' 49989
50137
SIDE Y ANGLE
49995 -59996' 49996 ^999r 49991 «9991 49988 «9988 49994 «9992 49992 « 49992 «9996 50020
50000 50000 50000 '50000 50000 50000 50000
TÜÜÜCT 50000
50000 "50000 90000 STHHJCT 90000
83
\
RUN A ANGLE LIFT DRAG PITCH YAW ROLL SIDE Y ANGLE
031 49940 50000 50001 49947 49998 50000 50000 50000 xsrt- - 49960 50000 50000 49969 49998 ' 50000 50000 50000 031 49980 50000 50000 49987 49998 50000 50000 50000 031 " 50000 50000 50000 49999 49998 50000 50000 50000 031 50020 50000 50000 50010 49998 50000 50000 50000 on 50040 50000 50000 50014 49998 5O000-- 50000 50000 031 50060 50000
-50000 50000 50000
50014 50010
49998 4999B
50000 50000 50000 50000*
50000 031 —50080 50000 031 50100 50000 50000 50005 49998 50000 50000 50000 on 50120 50000 50000 49992 4999fl 5OO01 50000 50000 031 501<*i 50000 50000 49976 49998 50001 50000 50000 031 501c 0 50000 50000 49956 49998 5000? " 50000 50000 031 5018L 50000 50000 49931 49998 50002 50000 50000 031 50200 50000 50000 49904- 49998 50007 50000 • 50000
RUN
032 032 032 0«~ 032 -052- 032 "052—
-051- 032 -052" 032 -05r 032
A ANGLE LIFT
49940 49132 UV95U 49552 49960 49562
' 49970 49980
49T76 49994 "50214-
50000 50440 -5U010 STTSTC" 50020 50886 90030 9T108
032 052 032 90040 51340
"052 90050—"515*4 032 50060 91762
900TO 90080 90090 90100 90110 90120
-5T59» 92212
-52*1«- 52634 925<0 93000
DRAG PITCH YAW
50118 49567 50025 5OT10 49603 5002*- 50102 49638 50025 50097 49670 50025 50093 49702 50028 50091 49T33 50028 50091 49762 50028
"5 0CPF3 4 97B7 5 0 07F" 50098 49812 50028
-50105 49555 50029 50113 49859 50031 50124 - 49879- 50OT1 50137 49898 50028 90191 499T6- 50025- 90166 49934 90032 90186 49949^ 90031 50206 49964 50029 50226 49977 50249 49987 50026
SIDE Y ANGLE ROLL
49987 49997 50000 - 49959" 49999 50000
49983 49997 50000 49976-49998 50000 49980 49995 50000 49978 49997 "50000 49974 49993 50000
"49973 '47994 '50000 49978 49994 50000 49981 — 49993 50000 49983 49993 50000 «9984 49993 50000 49978 49992 50000 49981 49992 50000 49979 49994 50000 499/6 49993 50000 49973 49992 50000 9986 * 49995 50000
49984 49994 50000
84
RUN A ANGLE LIFT DRAG PITCH YAW ROLL SIDE Y ANGLE
03« 49940 500O0 50000 49936 50000 50000 50000 90000 03« 49960 50000 50000 49962 50001 50000 50000 90000 036 49980 50000 50000 49982 50001 50000 50000 90000 038 50000 50000 50000 49999 50001 50000 50000 90000 038 50020 50000 50000 50011 50001 50000 50000 90000 038 50040 50*000 50000 50017 50001 50000 50000 90000 038 50060 50000 50000 50018 50001 50000 90000 90000 038 _ 50080 50000 50000 50017 50001 50000 50000 90000 038 50100 50000 50000 50009 50001 50000 90000 90000 038 * 50120 50000 50000 49998 50001 50000 90000 90000 038 50140 50000 50000 49983 50001 50000 90000 90000 ÖS8 ~ 50160 50000 50000 49962 50001 50000 90000 90000 038 50180 50000 50000 49938 50001 50000 90000 90000 «8 "50200 50000 50000 49908 50001 50000 90000 90000
V
RUN _ A ANGLE LIFT DRAG PITCH YAW ROLL SIDE Y ANGLE
099 49940 48798 50177 50969 »0018 49998 4999» »0000 039 49960 49912 50152 50264 »0021 49989 49998 90000 039 49980 49800 50197 50174 50012 49968 49999 90000 099 »0000 »0922 50199 50077 50020 49967 49994 »0000 099 »0020 »0828 50199 49978 50024 4999» 49994 »0000 099 »0040 »1996 50196 49869 50020 49960 49999 »0000 039 »•060 91894 50184 49799 50023 49966 49996 »0000 0i9~ ~JdÖ80 »2942 ' 50222 " 49618 50022 4997» 49998 »0000 099 »0100 »2802 50278 49*460 50023 49976 49999 »0000 099 »0110 »2996 50925 49984 49990 49999 90006 »0000 099 »0120 »3018 50406 49974 50020 »0021 49998 »0000 099 - _ »0190 »9160 50457 49998 50014 »0046 90002 90000 099 »0140 »9288 50508 49282 »0011 90097 90009 »0000
■W9 »0190 »9406 50561 49229 9001» »00» 1 90001 »0000 099 »0160 »9444
99494 50649 »0794
49199 49041
900»» »0009
»0076 »0074
90009 9000»
»0000 isr »OITO »0000 099 »0180 »9696 »0829 48666 »0036 49669 »0047 »0000 ^19 »0190 »9798 »0907 48966 90099 . 49976 »004» »0000 099 »0200 99698 51042 48499 90040 49092 »0060 »0000
85
RUN A ANGLE LIFT DRAG PITCH YAW ROLL SIDE Y ANGLE
040 49940 50000 90000 49941 50000 90002 90002 50000 040 49960 50000 90000 4996« 50000 90002 90002 50000 040 49980 50000 90000 49985 50000 50002 90002 50000 040 50000 50000 90000 50001 50000 50002 90002 50000 040 90020 50000 90001 50012 50000 50002 90002 50000 040 90040 50000 90001 90019 50000 50002 90002 50000 040 90040 50000 50001 90021 50000 50002 90002 50000 040 90000 90000 90001 90019 50000 5Ö002 90002 50000 040 90100 90000 90001 90012 50000 90002 90002 50000 040 50120 50000 90001 90000 50000 50002 90002 50000 040 90140 50000 90001 49985 50000 90002 50002 50000 040 901*0 50000 90001 49965 50000 90002 "50002 50000 040 90180 50000 90001 49940 50000 90002 50002 50000 040 50200 50002 90001 49910 '50000 ■50002 ¥0002" ~~50000
RUN
041 041 041 641 041 041 041 0«" 041 041 041 0*1 041
041 0*1 041
A ANGLE LIFT
49940 W6Ö 49980 50000 50020 50040 50060
TWW
48798 49516 49806 50526 50842 51950 51870
11174 50100 92884 folio »OSO 50120 59292
"RinO~ $9996 90140 99468
10 59996 90160 99990
"51170 59620 50180 59988
DRAG
50178 50152 50137 50132 50139 50157 50186 50225 50277 50311 50352 30428 50516 ?0S9) 50708 50794 50883
FITCH
50361 50269 50179 50073 49972 49871 49756 "<M2<r
YAW
50024 50024 50024 50024 50026 50027 50026
ROLL
49974, 49969 49970 49961 49971 49971 49967 T9#6r 49966 49969 50010_ 50109 50076 mrr- 50336 5öiÖ4- 49251
SlOE T ANGLE
49996. 49996 49995 49993 49995 49994 49994 49^94 49996 '49997 49997 4«992 50002
49996 "«♦for
90090
50000 50000 50000 50000 50000 50000 .30000 50000 50000 50000 50OO0 50000
looöo 50000 TOOOO 90000
a Att;
86
APPENDIX III EFFECT OF TRANSITION STRIPS
■Oi
20 1.0 0.8 0.6
16
12
OC, Angle of Attack, Degrees
-4
0.18 0.16 0.14 0.12 0.10 0.08 0.06 0.04
C-t, Drag Coefficient
^N
NJI ̂ 1 N rk N rH N rHl r
) f 0.02 0 >4
Figure 39. Effect of Transition Strips on Wing. (To Be Used For Increments Between "X" Series Runs Only)
87 A
JL
CL, Lift Coefficient
0.02
0. 8 0. 6 0.4 0.2 ( ) -0 .2 -0.4
OV-1, 1/7 Scale Series 1
Symbi
a
)ls Run
9X
8X
WF2 (Trans
WF2 (Trans
Off Wing &
Removed F
Fuselage)
s v o rom Nose G •nly)
ife
^s s s kv ^
\ ̂
^s \ s
j
\ V \
^ r ^s
\
0.1 -0.1 -0.2
C , Pitching Moment Coefficient
B
20 1.0 0.8 0.6
16
12
CC, Angle of Attack, Degrees
-4
1 -—_ > ^ \ v
^^ x X N v
X
\
N V
S X \
s
\ 1
4
1 \
/
0.18 0.16 0.14 0.12 0.10 0.08 0.06 0.04 0.02
CD, Drag Coefficient
Figure 40. Effect of Transition Strips on Fuselage. (To Be Used For Increments Between "X" Series Runs Only)
89 A
CL, Lift Coefficient
0.6 0.4 0.2
-0.2
C , Pitching Moment Coefricient m
B
Unclassified Sacurity CUssification
DOCUMINT CONTROL DATA - R&D (tmcurlly clmnlllemtlcn of Mil*, body ol mbtlrmcl and lnd»*tnt mtnolallen mull b« «nlartd wAan Ut» ormrmll report «a claaaJhatfJ
I. ORI0INATIN0 ACTIVITY fCeiporala author;
Grumman Aircraft Engineering Corporation Bethpage, New York
2a RCPOMT ttCUHITV C LAtllFICATION
Unclassified 2 6 aneuF
I. ntPtmj TiTUi
WIND TUNNEL TEST OF l/f 8CAIE MODEL OV-1
« OKICHIPTIVE NOT» fTriM ol npott and Inehialva da(aa>
Final Report S. AUTHONrs; ftaat nmm: Html naaia, Inlllml)
Shepheard, Fred W.
«. RIPONT DATI
December 1965 7a
11 • a. CONTRACT ON «MANT NO.
DA H-177-AMC-27l(T) 6. mmojKCJ NO.
TASK lEl25901Allt203
i^«;
USAAVLABS Technical Report 65-7 3
• ». 9TMIN RKVOHT NOT« (Any otfiar numkara «al mar ba multnad
10. AVAILABILITV/LIMITATION NOTICIt
Distribution of this document is unlimited.
ii. >TU It. SRONtONINO MILITARY ACTIVITY
US Army Aviation Materiel Laboratories Fort Eustis, Virginia
It. AMTRACT
Wind tunnel tests were conducted on a l/7 scale model of the OV-1 airplane to determine the power-off drag, lift, and pitching moment co- efficients of the model and its various components. Significant drag differences were measured between production canopy and nacelle config- urations and streamlined fuselage and nacelle configurations, but are not considered applicable for reasons explained In the report. No other significant drag differences were measured.
DD I JANM I 4/w Unclassified Seewitjr Clesslficatlofi
