Results of a landing gear loads test using a 0.0405-scale model (16-0) of the space shuttle orbiter in the Rockwell International NAAL wind tunnel (OA163), volume 1

• NA T IONA L AERONAUTICS AND SPAC E ADMINISTRATION i

)

(NASA-CR-147bll) RJ:!SULTS Of A LANDING GEAR

J

N77-13130 LOADS TEST USING A v . O~05-SCALE MODEL (16-0) ' He. Pt I '"r OF THE SP CE SHUTILE ClidITJ:!R IN lHE ROCKWELL 1\0\1'" ~o \ INTJ:!RNATIONAL NAAL WIND TUNIEL (OA163) , Unclas VOLUME 1 (Chrysler Corp.) 435 P G3/1b 581171l SPACE SHUTTLE AEROTHE RH O DVNAH IC O AT A REPORT ~.-9T.-9 iIMN a gem ent se rv ices JOHNSON SPACE CE N TE R

SPACE DIVISION ~." CHRYSLER

,,~ CORPORATION HOUSTON, TE XA S

; November 1976 DMS-DR-2289 NASA CR-147,611 VOLUME 1 OF 4 RESULTS OF A LANDING GEAR LOADS TEST USING A o.o405-SCALE MODEL (16-0) OF THE SPACE SHUTTLE ORBITER IN THE ROCKWELL INTEILIVATIONAL NAAL WIND TUNNEL (OAl63) by , R. Mennell Shuttle Aerosciences Rockwell International Space Division Prepared under NASA Contract Number NAS9-13247 by Data Management Services Chrysler Corporation Space Division New Orleans, La. 70189 for Engineering Analysis Division Johnson Space Center National Aeronautics and Space Administration Houston, Texas

L

HIND TUNNEL TEST SPECIFICS: Test Number: NAAL 751 NASA Series Number; OA163 Model Number: 16-0 November 25 through December 9, 1975 Test Dates: Occupancy Hours: 144 FACILITY COORDINATOR: AERODYNAMICS ANALYSIS ENGINEER: R. B. Russell J. Reichert Mail Code AC07 Mail Code BD02 Rockwell International Rockwell International B-1 Division Space Division International Airport 12214 Lakelvood Blvd.

Los Angeles, Calif. 90009 Downey, Calif. 90241 Phone: (213) 670-3343 Phone: (213) 922-3265 PROJECT ENGINEERS: R. C. Mennell Mark Nichols Mail Code BD02 Mail Code AD38 Rockwell International Rockwell International Space Division B-1 Division 12214 Lakewood Blvd.

International Airport Los Angeles, Calif. 90009 Downey, Calif. 90241 Phone: (213) 670-3343 Phone: (213) 922-2665 DATA MANAGEMENT SERVICES: Prepared by: Liaison--D. H. Hersey Operations--H. B. Meinders

Concurrence: ~ /~P'p';:::::>

Approved:~~~~~~~~=- ___ Manager N. D. Kemp, Manage ions Data Management Services Chrysler Corporation Space Division assumes no responsibility for the data presented other than display characteristics.

ii

RESUIJl'S OF A LANDING GFAR WADS TEST USING A 0.0405-SCALE MOllE!. (16-¢) OF THE SPACE SHUTTLE ORBITER Di THE ROCKWELL IBTERNATIONAL NAAL WIND TUNIiEL (0Al63) by R. Mennell Rockwell International ~ce Division Experimental aerodynamic investigat i ons were conducted on a sting mounted . 0405 sca l e representation of the 1400 outer mold line space shuttle orbiter configuration in the Rockwell International 1.15 x 11.00 foot low speed wind tunnel during the time period from 25 Novembe r 1915 to 9 Deo~ber 1915. NASA designation for this test period was 0Al.63.

Facility designation was NAAL 151.

The primary test objectives were to define the orbiter landing gear system pressure loading and to record landing gear door and strut hinge- moment levels.

Secondary objectives included recording the aerodynamic influence of various landing gear configurations on orbiter force data as well as investi gating 40' x 8 0' Ames Wind Tunnel strut s1mul.ation effects on both orbiter landing gear loads and aerodynamic charact. eristics.

Testing was conducted at a Mach nUlllber of 0.11, free stream dynamic pressure of 42.5 PS1', and Reynolds number per unit length of 1.2 x lr::P ~r foot. Angle of attack variation was 0 to 20 degrees while yaw angles ranged from -lO to 10 degrees.

iii

I

, TABLE OF CONTENTS Page ABSTRACT iii INDEX OF MODEL FIGURES INDEX OF DATA FIGURES NOMENCLATURE CONFIGURATIONS INVESTIGATED TEST FACILITY DESCRIPTION DATA REDUCTION REMARKS REFERENCE ~ TABLES I. TEST CONDITIONS II. DATA SET/RUN NUMBER COLLATION SUMMARY III. MODEL DIMENSIONAL DATA FIGURES MODEL DATA APPENDIX - TABULATED SOURCE DATA FORCE DATA (VOLUME 1) PRESSURE DATA (VOLUMES 2, 3, & 4)

I

.

INDEX OF MODEL FIGURES I

, -

Page Title Figures Systems and Sign conventions.

1- Axis a. Axis Systems.

Sign Convention tor Control SUrfaces.

b.

Model sketches.

2.

NAAL Tunnel Installation.

a.

Model Base Pressure Instrumentation.

b.

- 35 Sign Convention for Landing Gear.

c.

L.R. NlG Door Pressure Instrumentation.

d.

L.R. MIG Door Pressure Instrumentation.

e.

L.R. MIG Strut Pressure Instrumentation.

f.

g. TYPical Landing Gear Strut Strain Gage Instrumentation.

Typical Landing Gear Door Strain Gage h.

Instrumentation.

Model photographs.

3.

NAAL Installation, Front Vil!!ll, Model a.

Configuration B68Cl2G2OMl6N28wl27E55FlOV8R5X9.

b. NAAL Installation, Rear View, Model Configuration B68Cl2G20Ml6N28w127E55FlOVSR5X9· NAAL Installation, Bottom View, Model c.

Configuration B68C12G2OMl6N28wl27E55F1OV8R5X9.

QW'" loBO, ¢N = 66° .

d. !lose Landing Gear,

Main lAnding Gear, QM = 35°, ¢M = 88 •

e.

f. NAAL Installation, Side View, Model Configuration B6 8C l2G20N 16N28Hl 27E55FlOV8R5X9 - + 40' x 80' Strut Simulation.

A ,,~-,~,- ••• ,' ~~-."'- ..

~

t----

•• "-<-,,- 1-136 PAGE 248-253 254-259 266-269 274-281 137-241 242-247 260-265 270-273 282-285 ~- C G G G A B D E F G PLOTTED .~~_~_ SCHEDULE COEFFICIENT SPDBRK ,SPDBRK ALPHA ALPHA ALPHA ALPHA "-""""'_L ....

BDFLAP BDFLAP, __ BETA, BETA, BETA, BETA, BETA BETA BETA BETA ..

VARYING CONDITION _~""_~ .........

BETA,CONFIGURATION, ELEVON, ALPHA,CONFIGURATION, ELEVON, FIGURES ~ .....

DATA HINGE GEAR GEAR OF + PLANE PLANE HINGE DOOR DOOR STRUT INDEX LANDING LANDING --1"& • GEAR STRUT GEAR GEAR - - W/GROUND W/GROUND COEFFICIENTS STRUTS GEAR DEPLOYED -- AERODYNAMIC LANDING LANDING LANDING TITLE FULLY SUPPORT ----- AERODYNAMIC NOSE LANDING MAIN MAIN COEFFICIENTS COEFFICIENTS COEFFICIENTS COEFFICIENTS GEAR

DIRECTIONAL L.H. NOSE L.H. L.H. ~>->

MOMENT MOMENT MOMENT DEPLOYED MOMENT MOMENT MOMENT

,,'

SIMULATED

__

LANDING , COEFFICIENTS LONGITUDINAL LATERAL ORBITER HINGE ORBITER MOMENT ORBITER HINGE ORBITER MOMENT HINGE RETRACTED HINGE FULLY HINGE - HINGE AND 5 6 7 8 9 10 11 12 FIGURE NUMBER

______

w

___

!

INDEX OF DATA FIGURES (Concluded) PLOTTED COEFFICIENTS SCHEDULE: A) CAb' CAr' CN and C versus a m (:!

versus C ' Cn(BODY) and C~(BODY) B) Y i versus C) C ~N hND C versus D) eN hNS E) Ch~"versus ~M versus F) C eM hMS versus a C and C G) C ' C ' hMS hMD hND hNS ( , ,

''-.:'' , ,,-

"--'~-'-- -------~..--.-. -

NOMENCLATURE L; General . SYMBOL MNJj:MONIQ DEFINITION a speed of sound; m/sec, ft/sec Cp CP pressure coefficient; (PJ. - p",)/q M MACH Mach number; Via 2, p pressure; N/m psf q Q(NSM) dynamic pressure; 1/2 v2, p N/m , psf Q(PSF) PJI/L PJI/L unit Reynolds number; per m, per ft V velocity; m/sec, ft/sec ct ALPHA angle of attack, degrees BETA {J angle of sideslip, degrees PSI angle of yaw, degrees I/J . PHI r/> sngle of roll, degrees p mass den;ity; kg/m3, slugS/ft3 Referenc~ & C.G. Definitions 2 , Ab. baae ares; m ft2 b BREF wing spaD or reference span; m, ft e.g.

center of gravity LREF reference length or wing mean

~REF

c aerodynamic chord; m, ft S SREF wing area or reference area; ft2 m , MRP moment reference point XMRP moment reference point on X axia YMRP moment reference point on Y axis ZMRP moment reference point on Z axis SUBSCRIPTS b base local s static conditions total conditions free stream

'"

NOMENCLATURE (Continued) SYMBOL MNEMONIC DEFINITION balance cavity area, f't.2 ABC normal force CN normal-force coefficient; CN qS axial-force coefficient; axial force CA CA qS aide-force coefficient; side force Cy CY qS base force C CAB base-force coefficient; A qS 'b CAF forebody axial force coefficient, CA - CAb CAf pitching moment C CLM pitching-moment coefficient; m qS.II.

REF yawing moment Cn(BODY) CYN yawing-moment coefficient; qSb body axis rOlling moment , C9, (BODY), CBL rolling-moment coefficient; qSb body la,Xis CHMXY landing gear door or strut hinge moment Ch xy

coefficient = HMXY * 1000

qS .ll.B HMXY HMXY landing gear door or strut hinge moment, in-lbs xy xy letter designation for landing gear component = NS, nose landing gear strut = MS, main landing gear right hand strut = ND, nose landing gear right hand door = MD, main landing gear right hand door DUMMYl artificial geometric variable/dimension DUMMY2 used as second dimension in datasets containing perimeter and strut pressure taps fuselage reference length, in

NOMENCLATURE (Concluded) SYMBOL MNEMONIC DEFINITION TAP pressure tap number, Figures 2d,e,f give locations X/CML longitudinal position along main landing gear door, as a fraction of it's length longitudinal position along nose landing X/CNL gear door, as a fraction of it's length Y/BML lateral position across main landing gear door, as a fraction of it's reference width Y/BNI, lateral position across nose landing gear door, as a fraction of it's reference width body flap deflection, degrees BDFLAP ELEVON elevon deflection, degrees SPDBRK speed brake deflection, degrees THETAN nose landing gear strut position, degrees THETAM main landing gear strut position, degrees PHI-N nose landing gear door position, degrees PHI-M main landing gear door position, degrees main landing gear strut pressure orifice location, degrees CL lift coefficient; l~§t drag coefficient; drag CD qS base drag CDB base-drag coefficient; qS CDF forebody drag coefficient; CD - CDb yawing-moment coefficient; yawing moment, CLN stability axis qSb rolling-moment coefficient; rolling moment, CSL stability axis qSb center of pressure location referred to ~b XCP/L

CONFIGURATIONS INVESTIGATED

J

The model provided for test period OAl63 was an .o405-scale repre- sentation of the l40c r 'J2ce shuttle orbiter outer mold line configuration.

The ~asic model was of the blended wing-body design utilizing a double delta wing (75°/45° A • ,), full span, dual panel elevons (unswept hinge- L E line and Gil gaps), a centerline vL'rti'lal tail with rudder and/or speed brake deflection capability, a canopy, a body flap, and an orbital maneuvering system (OMS puds) mounted on the aft fuselage sidewalls ad- jacent to the vertical tail. Landing gear simUlation consisted of both nose and main landing gear systems each with the deployment capability from full up to full down.

Floth the nose and II1E'.in landing gear systems were instrumented with static pressure mea~u.·ing orifices and hinge moment beams as illustrated in figures 2 c through 2h.

For this test period the following nomenclature was used to desig- nate various model components: Component Description B68 l40c orbiter fuselage with air vent door and vent door probe simule.tion Cl2 l40c orbiter canopy E55 l40c orbiter dual panel elevons FlO l40c orbiter body flap G20 l40c orbiter nose and main landing gear system simUlation Ml6 l40c orbiter OMS/RCS pods -"-=-'-:

CONFIGURATIONS INVESTIGATED (Concluded) Component Description 140c orbiter OMS nozzles N28 140c orbiter double delta wing IVl27 140c orbiter rudder R5 140c orbiter centerline vertical tail v8 X9 transition grit Designated configuratiG~s are:

o _ B68 C12 E55 FlO MI6 N28 R5 v8 W127 X9

GP Ground plane installed SS _ Strut simulation (40' x 80' Ames Wind Tunnel) I .\.

-----------,--_.- --- ---_\-'-"'-~- ---- -

j I REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR

I

I

I

, TEST FACILITY DESCRIPTION North American Aerodynamics Laboratory (NAAL) 7.75 x ll-foot Wind Tunnel is a continuous flow, closed circuit, single return tunnel capable of sPf!eds up to 200 m:J.lcs per hour.

The test section is vented to atmospheric pressure and is 7.75 x 11 feet wide and 12 feet long. Power is supplied by a 1250~horsepOwer na~ celle-mounted synchronous motor drivjng a 19-foot, seven-blade, leminated birch propeller. Airspeed is controlled by using a magnetic clutch to vary the degree of coupling between the motor and propeller. Turbulence is minimized by a damping screen and a honeycomb section in the settling chamber upstream from the contraction cone (ratio 7.53 to 1).

Tests may be conducted using a variety of mounting systems: sing:!.e strut, double strut, sting strut, reflection plene, cable suspension, or two-dimensional ;mll. Aerodynamic data may be measured by a plenar type external balance system or sting-mounted internal balances. An ABtrodata Automatic Data Acquisition System collects, multiplexes, digitizes, and reCords on magnetic tape 50 channels of force or pressure data or both.

Data are then reduced and plotted using automatic data processing equip- ment and an automatic digital plotter.

The NAAL Wind Tunnel has been operating since June 1943. Ce.libra- tiona are availeble over a wide range of test conditions.

'I'

"'-' ,,'

DATA REDUCTION The aerodynamic force data presented in this report was measured by the Task Corporation 2.5 inch MK IX six-component strain gage balance.

All steady state static pressures were measured by ~2.5 psid Statham differential pressure transducers installed in a four-pack model mounted scanivalve referenced to tunnel static pressure. Landing gear strut and door hinge moment loads were measured from single beam, bearing mounted strain gages.

Corrections applied to the aforementioned data were test section wall effects on model aerodynamic coefficients, model tunnel blockage effects On test section dynamic pressure, model base pressure drag effects on model angle of attack and angle of sideslip.

.~ Nose and main landing gear door static pressure tap locations are presented non-dimensionalized by landing gear door total chord or span.

The coordinate systems used have origins at the fonrard outer corner of each respective door. Tap locations about the door perimeters and left main landing gear are presented by tap number only.

The following reference dimensions and constants were used in data reduction: Model Full Scale .., Symbol Scale area of model base, (not including ABC), ft2 0.5885 area of balance cavity, ft2 0.0985 ,ling span, in. 936.68 b 37.9356

DATA REDUCTION (Concluded)

]

Model Full Symbol Scale Scale left main landing gear door bML reference span, in.

2.794 68.99 landing gear left nose door bNL span, in.

reference 1.154 28.49 wing c MAC, in. 19.2300 474.81 left main landing gear door cML reference chord, in. 6.116 151.01 left nose landing gear door cNL reference chord, in. 108.47 4.393 S wing area, ft 4.4123 2690.00 reference C.G., fus. sta. 1076.68 J<MRP 43.6055 ZMRP reference C.G.waterplane 15.1875 375·00 orbiter body length, in. 52.2572 1290.30 1.B The plotted and tabulated data are arranged in the following manner: VOLUME NO.

Data Figures Tabulated Force Data Fourth Tabulated Pressure Data

Character *

2 Nose landing gear door outer surface N landing gear door inner Nose surface E Main landing gear door outer surface M Main landing gear door inner surface F 4 Nose and main landing gear door perimeter P Main lanJing gear strut W

* The fourth character in each dataset identifier (i.e., RFFPXX, for

perimeter) represents the individual component.

.

REMARKS

-'

All landing gear pressure data obtained in this test program showed good agreement with predicted data trends and evidenced excellent repeat- ability. No anomalies occurred in their acquisition or reduction.

Likewise, excellent behavior was experienced with main balance and landing gear door hinge moment deta. These were acceptable for immediate reduction and presentation after the test.

Nose gear strut trunnion-moment outputs Were also notable for their repeatability and consistency with expected trends, although the absolute magnitude of these loads data was almost ~ouble what had been predicted prior to the test.

Main gear strut trunnion-mome'1ts also exhibited exceptional repeat- ability, hoth in testing and in all pre- and post-test calibrations.

However, unusual behavior was observed in the data obtained for the full- down strut position (and somewhat at the 80 settin~). Plots of hin~e moment versus strut posit.ion showed a hook in the vicinity of t.he fully extended posit.ion. After close examination, this "as attribut.ed to the fully-extended main gear drag link taking up part of the strut load when the strut was deflected under load. Initial calibrations of the strut hinge moment gage were done with the drag link removed. The gage was recalibrated "ith the drag link installed. This calibration was used again to reduce the test data. These data are presented in this report.

REFERENCE ].

AD75-SH-0238, "Pretest Information For A Landing Gear Loads Test (0A163) Of The 0.0405-Scale Model Of The Space Shuttle Orbiter In The Rockwell International NAIlL Wind Tunnel (Model 16-¢)," November 10, 1975.

TABLE I TEST: 0A163

I DATE

~1/6h6 TEST CONDITIONS REYNOLDS NUMBER DYNAMIC PRESSURE STAGNATION TEMPERATURE MACH NUMBER (per unit length) (degrees Fahrenheit) I 0.17 1.20 x 10 1ft.

42.5#/fi?

80 -120~ BALANCE UTILIZED: 2.:2" MK IX COEFFICIENT CAPACITY: ACCURACY: TOLERANCE: 1500# each gage ~,25~ NF 'l'ioff SF each sage ~,22~ + 20'0# each gage

AF -,25i

PM RM YM COMMENTS: I . - .

- ... ----.---~

_~_--=""''''''-'-

-d- _

t

~~

ot:;l >dO ~K1 il;t=i 13'8 _.

>d~ E:ic::

z;g

~~

~~

7=°

I -,.-~,-" " m '" ~ II c z z c ~ III n .' 76 ...

, NC'V -~ J ,

-,--

2.

II Ie, 7"1

/0 <;. 3' "1t.. 7~ ~'/

.;«(., 1S'1 60 fD1 ~ ""I :11 IS,,! 5$" (2)

PM

7' I.:t., 11

.s 4(7

.:1< 7.3 IDVAR

~7 3.1.. So<f 7r? ~..3 9.,3

1!>7? IS3 s'i ~~ n

--;;r.L

'76 /11 .{ i A.

IDVAR I g r£8. Ie 13 33 7.J. 71 'i?.:I.

.;?3 :18' "If? $G' (;.7 'f17 q~ fS!>- IQ.,Z .5".3 0.5',10

"

S.E.T 4{l(."''£'' 8/£7~ !.z -2- , IDATE: -~-,

"

l' !CAB..

cf &?I '<I 19 ~tf .?'t 71 7(" li'1O 91 ,341 '"19 S~ Is7 lSI ";;3 -s .

Q-P,;{o° -/~, ..

- 35' $ 6"0

10 IS- ao 3D 70 7 ru,- 90

:!IS .!>-o ISfa 5"1 ISO SIC ~.1..

-10

I )

""J"" ' JX.c.P/.L ~ {- S" SUMMARY 0" I}dc_= 1./ /.ft> r3f..1 3.1 .;BrD)::: 1,1 ~.2. .1..0 3~ //.2- So (,~- so . , • J3 TION 4 &, .1 0" 11 • 10 I!'- ;10 ~ .,q ~o A 3~..l.1 "Ii'.3 1~1 ICY II.

S

~

~ I ~ COll 0" ;( 9.'i1 /.3 10 (oS If 01 :<.''1 35" S/J ,_",_.,_,~"",,_ TABLE Z ~ ~ q cO 0° 10 IS" 37 ¢",.

.~G, :1.0 30.S .5"0 I , !C.5,L,.

NUMBER .;lO zS P-'9R.4HET~-;e .

COEFFICIENTS RUN

o·

"

l'BFL&il CLN

'"

SET

o·

IJ,,- ";8,IO,Ib, ./7 DATA ,,"S 4t><::~ ICA.F .

S; II .

<XM

/0 II F £et-l/).

......

(N.

0,2,1 :: A LM.

oil \

03 .x!i3):.

&C () CO"4F!GURATION -.

fJ , !);:}/(};, OR ,-!CDF SET /0 1/ 1'< 1..3 O'f (Xp 03 07 It "'-'

OS /7

N? 09 1</ IS Ito CIt -:0:< I SCHEOULES DATA IOENTIFIER TEST: Rrrloi , C.L,

""

I-"

. I:H

< < ~ '" ~ ~ c z z c :r 7•

~ -

ov t-!

I

- :, 11"1 (1"1 IZI ;09 137 14'1 ,~ IJ4 IfD'I 17K I~S l'i/ :.ul ;Ul

171 :uo :1.13

;1.15

I-IA

P

vAR S" rli , lo

113 '''3

/3;:' 1J}j' If?'{ 1'(0 113 I,z,to 170 108 177 :J.o't :zoJ? ;1.07 ).05 ..

1.41 2,oto '7~ .;2 1\1 I~3 1~'1 171.

I i A.

Z.

QVAR ~.1. I o r"£d.

N7 1/2.. /'11.

13:). /07 I" 111>8 I 137 1.1.7 I~'i 19.2. 1'1.2.

I7S /9.2. 1'13 19'/ •• J1£T 6'ET4 7 TE: .

-~ IfD 1 I~( (~l?

DA I

"

I.

/'(ro III I.lK

-s tJi ,.3(0 NI /4. 173 190

lOft I"" In 199 197

1'15' 19/Q 195 'I " .

,'{~

-It) IO!>- /10 1.1. ,n IfffD

130 1.3.;,- lifO 1.(,,0 1~5" ' ::J.OO ~Ol .;lOA. ;J.03 /1-< .;lO~ ..

' 9 I MMAR Y SU 0 10 IS" 'Ill ~o 9", ..

-c 8~ .::

"

loSH 1 Continued - ...

(OLLATlnN 9 '1S K{C ,(lg

.s

II.

....

3" 4>h I l,s"

2b +

8S 0 TABLE 85 ~!: 1,(<.>1 COEFFICIENTS rAnAI1t£r~~ RUN NUMBER I

l

0" 0 +

IS' i/.l //.l :5:,'"

"

7/.7 I.(AF ~.

• 1 ~

• l

()O &...:.

S 0 /0 0 -;0 ..2, IJ.E

•

~ ~ .17 DATA SET

Ilf "

I -.1, c 0( A 8 /Q" ttl). c;.

D sc F E . F -.5;

I

IP

MM -

' 9 CJj -/~ -t.O =

=

.ON .

MAt!).

d(t.l GLJ~A:

" 70(1£2

c.:1J

6P GP+55 ''IFI ....

:-C' NoS.

OT

o

f3 , (:/{jA CULE':: 01';

0A/o3 . .•

IER E S,ET J7 ~ J.fL> ).f{ 30

.;12. ..u J~ 31

.;1./ ~'l (J )1<1 J.;/C SCH A'TA ENTtF" Q lO TEST: RFF • IL

V:JiMJJ.D

.... " ..

TABLE II. - Concluded.

Definition of DATASET IDENTIFIER 4th Character (i) 4th Character Type of Data Force Data

o Aerodynamic force coefficients

Left nose and main landing gear H door and strut hinge moment coefficients Pressure Data N Left nose landing gear door outer surface static pressure coefficients E Left nose landing gear door inner surface static pressure coefficients M Left main landing gear door outer surface static pressure coefficients F Left main landing gear door inner surface static pressure coefficients P Left nose and main landing gear door perimeter static pressure coefficients

w Left main landing gear strut static

pressure coefficients

--------"'.c,~: _

I [ , !

u; TABLE III.

MODEL DIMENSIONAL DATA MODEL COMPONENT: __ BO_D_;Y_-_B6~8~ ______________ _ GENERAL DESCRIPTION: Configuration 140c orbiter fuselage. Similar to 140A/B fuselage except aft body revised and midbody-wing glove area modified. B68 has the addition of air vent doors and air vent door probes.

MODEL SCALE: 0.0405 DRAWING NUMBER: VL70-000140c, -000202C, -000205A, -000200B, -000203 DIMENSIONS: FULL SCALE MODEL SCALE Length (IML: Nose @ Xo = 238), In. 1290.30 52.257 Length (OML: Nose @ X In. 12 = 235) , 52.379 23.30 a Max Width (@ Xo = 1528.3), In. 264.0 2 10.62 Max Depth (@ X = 1464), In. 250.00 10.125 Fineness Ratio 4.899 4.899 Area _ Ft Max. Cross-Sectional 340.89 0.559 Planform Wetted Base .7

TABLE III (Continued) MODEL DIMENSIONAL DATA MODEL COMPONENT : __ ~CA~N~Off~-~C~la~ ________________________________ GENERAL DESCRIPTION: Configuration 140C orbiter canopy, vehicle cabin No. 31 updated to MCR 200-R4. Used with fuselage 86 •• MODEL SCALE: 0.0405 DRAWING NUMBER: VL70-000140C. -0002028, -000204 DIMENSIONS: FULL SCALE MODEL SCALE 5.806 Length (XO = 434.643 to 578), In. 143.357 6.173

Max Width (@ Xo = 513.127), In. 152.412

Max Depth (Zo = 501 to 449.39), In. 51.61 2.090 Fineness Ratio Area Max. Cross-Sectional Planform Welted Base ....~~.;

----

REPRODUCIBILITY OF THE TABLE III (Continued) fHTGINAL PAGE IS POOR HODEL DJ1.!ENSIONAL DATA .

,

I L·

MODEL COI-1PONENT: \,- '-- GENERAL DESCRIPTION: Configuration IhPC dual panel elevon.

Elevon hinge- line at Xo = 1387.

Elevon split line at

YO =

to 312.5.

Upper wing/ elevon ~p sealed Iby flipner doors, HODEL SCALE: 0.0405 DRAWl NG NUMBER: VL70-o00140C, -006089, -o00200B, -006092 DIMENSIONS: FULL~SCALE MODEL SCALI; _ Ft Area 210.00 0.344 Span (equivalent) , In.

349.20 14.143 Inbld equivalent chord, In.

118.00 4.779 OutbId equivalent chord, In.

55.19 2.235 Ratio movable surface chordl total surface chord At Inbld equiv.

chord 0.210 0.210 At OutbId equiv.

chord 0.400 0.400 Sweep Back-Angles.

degrees Leading Edge 0.0 0.0 Tailing Edge - 10.056 - 10.056 Hingelia e 0.0 - 0.0' Product of Area & c) Area 3 Moment (~~), Ft 1587.25 0.1054 \ Mean Aerodynamic Chord, In.

90.70 3.673 --' ...

-,-._'-- .-,.--

~ !II (Continued) MODEL DIMENSIONAL DATA

· 1

I ,./ I

MODEL COMPONENT : ____ ~B~OD~Y~FLA~P~-~Fl~O~-------------- __ __ GENERAL DESCRIPTION : _~C!!;o::!n::fi:fg~u::.:ra.~t~i~on~1:!±40:::::C~b::::od~;rL.:!:f:!la.::tp~ • ......!H:!:ing:!§:e:::1:.::in~e=-_ located at X = 1532, Z = 287.

o

i DRAWING NUMBER: VL70-000140C. -355114 DIMENSIONS: FULL SCALE MODEL SCALE Length (X =1525. 5 to X =1613). In. S7. 50 3. 544 O O 10.368 Max Width (@ L.E .• Xo=1525. 5). In. 256.00 Max Depth (XO = 1532). In. 19.798 0.802 Fineness Ratio Area 35.196 0.058 Max. Cross-Sectional (@H.L.)

135.00 0.220 Planform Wetted Base (XO = 1613) 4.89 0.008

TABLE III (aontinUl'!d) 110DEL DIMENSIONAL DATA MODEL COMPONENT: Landing Ge&l:' - G20 GENEHAL DESCRIP'l'ION: S19 modified to conform to updated drawings V070-510001 and V070-510501. including web-simylatiQn.

Mop.el Scale = .Q. QM) 5

Drawing Number: _ V070-5JQOOl, V070-510501 DL'!ENSIONS : FULL SCALE MODEL SCAm NCSE UNO It{G GEAR STRUT Number J J Dia.meter in.

6.b2Q o.?60

Length in.

63.704 2.580 Exposed Pivot Point to Wheel Axis 76.543 3.100 Pivot Point Location in.

Xo :m.2Q6 J 2. 2Q6 ]2.069 ~.ooo Zo "/HEELS Number Diameter in.

J.3QQ 2~.Q22

-

Wid~h in. Q./,QQ 2.8?Z Axis Location in.

370.167 14.992 Xo 0.0 0.0 Yo 221.643 8,2'77 Zo DOORS Side

Number 2. _-s

-

Length in. 108.4:r 1.·:22:2 Height in. 0.82 2 20. !2i!:2 Area Ft Hingeline LoC6\tion Xo + _....-II ........ ] ",54",-_ Yo

+ ze·494

)Ol.[36 ]2.224.- Zo End Number NONE NONE Length in.

Depth in.

Areo. Ft2 Hingeline Location Xo Yo Zo IS~ 485-1 Exp. 11/27/73

TABLE :!II (Continued) lAnding fV[ODEL COMPONENT: Gear - G ao,_(~C;;;o;;;:n~tin:;;;;;u;:e.:;:d~) ___ ~ ______ _ D I/olENS IOIIIS : FULL SCALE MODEL SCAm MAIN LA...lIDn.'G GEAR ST!lUT Number 2., __ l:iameter in.

9·383 Q.300 Length in.

Exposed

87.2

J.560 Pivot Point to Wheel Axis .107.901 4.370 Pivot Point Location in.

Xo 1180.0 47.790 Zo 283.012 4.462 WHEELS Number .

Diameter in.

• k9.383 2.000 Width in.

_17·778 0.720 Axis Location in.

Xo 1172·413 47.485 Yo

± 136.000

±_

5.508 Zo JJ5.372 _-L. 7 ,"",1'.!.!0l- DOORS Side Number Length in.

151.012 6.116 Height in.

62.469 2.530 Area Ft2 Hingeline Lo08tion Xo Yo + 174.000 + 7.047 Zo 282.148 1l.427 END Number NONE NONE Length in.

Depth in.

Area Ft2 HL1geline Location Xo Yo Zo

TAELE III (Continued) MODEL DIMENSIONAL DATA MODEL COMPONENT : __ O~MS~P~O~D~-~Ml~e~ ____________________ ___ GENERAL DESCRIPTION: ---l19nfiguration MOC orbiter OMS pod - short pod.

MODEL SCALE: 0.0405 VL70-00$401. -00$410 DRAWING I,~UMBER : DIMENSIONS: FULL SCALE MODEL SCALE Length (OMS F\.id Sta. XO=1310. 5), In. 25$.50 10.469 Max Width (@ Xo = 1511), In. 136.8 5.540 Max Depth (@ Xo = 1511), In. 74.70 3.025 Fineness Ratio Area _ Ft 58.864 0.0966 Max. Cross-Sect;"nal Planiorm Wetted Base , '-.,' -------=-- -,

~

TABLE III (Continued) MODEL DIMENSIONAL DATA MODEL COMPONENT; _OM_S_N_0_Z_'lJ_J_'!S_-_N~2~8l- _____ . ____________ , GEllERAL DESCRIPrION: Configura.tion 140C .' orbiter OMS Nozzles.

, !

----------------------------------------------------

MODEL SCALE: 0,0405 DRMIING NUMB&."l: --11L70"()00140A (Loea tion 1, SS-A00106, Release 5 (Contour) DIMlliNSIONS: FULL SCALE MODEL SCALE MACH NO.

Length - In.

Gimbal Point to Exit Plane Throat 100 Exi t Plane Diameter - In.

Exit Throat Inlet Area - ft2 Exit Throat Gimbal Point . In.

(Station) Left ~ Nozzle 1518.00

Xo 61.479

- 88.0 - 3. 564 YO

Zo 492.0

19.926 Right..f@oot Nozzles

;; . ."-_,'<.;~'W; X6

151,8,00 6].1+79 88.00 YO 3.564

z

1..92,00 _19.926

°

Null Position - Deg.

Left ~ Nozzle Pitch 15°49' 15°49' Yaw 12 17' 12 17' Right ~ Nozzle Pitch 15°49' 15°49' Yaw

-..1. °17'_ 12°17'

J

TABLE III (Continued) MODEL DIMENSIONAL DATA , '-..- . ..- MODEL COMPONENT: RUDDER - R5 GENERAL DESCRIPTION: Confi~uration 140C orbiter rudder (identical to configuration 140AtB rudder).

MODEL SCALE: 0.0405 DRAWING NUMBER VL70-000146B, -000095 DIMENSIONS FULL SCALE MODEL SCALE _ Ft 2 Area 100.15 0.1643 Span (equivalent) , In. 201.00 8.141 Inb'd equivalent chard 91.

585 3.709 Outb'd equivalent 50.833 chord 2.059 Ratio movable surface chord/ total surface chord At Inb'd equiv. chord 0.400 0.400 0.400 At 0.400 Outb'd equiv. chord Sweep Back Angles, degrees 34.83 Leading Edge 34.83 Trailing 26.25 Edge 26.25 Hingeline _ 83

211:. 34.83

(Product of Area & c) Area Moment ~) 610.92 0.0406 ,Ft Mean Aerodynamic Chord, In.

73.2 2.965 , .-.~---~-"-~" '-',~ -~..: .. ,-,,-~,,".----~.--¥---'" -~'-'~------ .. _ .... .....--.- ... -- ,,-,'--" ----------

III (Continued) TABLE DATA DIMENSIONAL MODEL - VS VERTICAL COMPONENT: MODEL --------~--------------------~------ tail (identical vertical orbiter 140C Configuration DESCRIPTION: GENERAL tail).

vertical 140A/B configuration to 0.0405 SCALE: MODEL 70-o00146B VL70-o00140C.

NUMBER: DRAWING SCI1,LE MODEL FULL SCALE DIMENSIONS: DATA TOTAL - Ft Area (Theo) 0.67S 413.253 Planform 12.7S7 315.72 - In.

Span (Theo) 1.675 1.675 Aspect Ratio O. 507 O. 507 Taper Rate of 0.404 0.404 Ratio Taper Degrees- Sweep-Back Angles, __ hl..Q,0!!- 45.00 Edge Leading 26.25 26.25 Edge Trailing 41.13 41.13 Element Line 0.25 Chords: 50 10.B74 2M.

~-IP Root (Theo) 4.393 10S.47 I>JP Tip (Theo) S.092 199.S1 MAC 59.272 MAC 1463.35 Sta. of .25 Fus.

25.73S 635.52 of .25 MAC W.P.

0.00 0.00 of .25 MAC B.L.

Sec t lon Airfoil 10.00 - Deg. 10.00 Wedge _~ngle Leading 14.92 Angle - Deg. 14.92 Wedge Trailing O.OSIO 2.00 Leading Edge Radius 0.022 13.17 Void Area

------

0.0 0.0 Area Blanketed ; I I I

28 J

\

TABLE III. (Continued ) MODEL DIMENSIONAL DATA ~OEL :?~ON~T:, __ ~W~IN~G~-~W~ln~ ____________________________________ __ ~SI S ~ . _ DESC~: on Ct\ :. __ --'c:.:o;:.:n:.;rig=ur:.;&::.;t:.:i:.:on~1A=OC~o;.rb;;:i;,;:t;;er:...;wing="',I....:.:MC;::R:...:200;;:..-.:;R4=, ..:".::1 m=l:;:'=&=-r ...;t:.:o~ 140A/B wing l ' ~ll~ but v,ith ref1nement" improved Wpg- bopt=lJ)idhody fAiring (X = 9l.0 g to Xo c 1040); elevon solit line relocated trom Yo - 281 to YO = 312.5.

M O DEL SCA LE : 0.0405 -;:S~ ~a.

OIIG.

NO. VL70~1AOC, ~200B DIMENSIONS: FULL-SCAlE MODEL SCALE TO,AL OA"':A Area (. ,eo.)

Ft ?lanform 2~2Q . 00 4.412 S?an ( Theo In.

2J6.68 n9~6 As?ec'; ~atio 2.265 2. 2 5 ~ate of Taper ~,12Z 1·177 Ta~er Ratio

Q.m

P e?OQ Dihedral Ang~e, degrees 3,500 JI~ Inc ;dence k~g l e, degrees Q.~~ g. sgg Aerodynami c Twi st, degrees Swee? 3ack Angles, degrees Leadi ng Edge ~2.QQg 4 '000 Trail ing Edge - - 10.056 12.Q2Q 0.25 Element Line 5. 209 35,209 Chords: Root (Theo) B.P.O.O.

~§2.~ Z7. 4 Tic, (Theo) B.P.

~J21a2 5,581 MAC 19,210 M:Zl! I t!l Fus. Sta.

of .25 MAC ll3gd~J 46,042 W.P. of .2.5 MAC 1LZ69 '2Sl.

~a B.L. of .2.5 MAC 182 13 7 736 EXPOSED DATA Area (Theo)

Fl

1751. 50 2.87~ Span. (Thee) In. BP108 7~.bEJ 29.1B Aspect Ratio 2.052 2.059 Taper Rat10 0.245 0.34 5 Chords Root BP108 562.09 22.765 Tip 1.00 b Ij7.S5 5. 5BJ MAC 2: 15.910 lr8~ Fus.

Sta. of .25 MAC

II 2.2 48.032

W.P.

of .25 MAC 1l.919 22!t ·JO B.L.

of .25 MAC ]0,1<77 ~21122 Airfoll Section (Rockwell Mod KASA) XXXX-64 Root b • 0.113 0,111

'2'

T1p b • 0.120 0.120 '2' ~ta for (1) of (2) Sides Lead'ng Edge Cuff 2 Pla"fc~;n Area Ct SILlS le2ding Edge I"ter~ects cus M.

L. 8 Sta

00 00 ~:~~

2 .

Leadi"9 Edge I"tcrsQets 'J1"!l ~ Sta 10 00 24.

41.472

TABLE III. (Concluded) MODEL DIMENSIONAL DA:J!A MODEL COMPONENT: TRANSITION GRIT - X9 GENERAL DESCRIPTION: Grit located on model nose and all swept surfaces to provide forced boundary layer transition.

NOMINAL GRIT DIAMETER - IN.

Fuselage All surfaces except fuselage STRIP THICKNESS - In. 0.10 LOCATION: Inches aft of local leading edge (streamwise) 1.00

~ Zw l I ...

I C

c

Cn,w @ yw m,w C /

Cc

Conventions

Cn,s

N s Sign z l C

I I ms

I C e

l

~

_ Syst n C

~

Axis Systems and s x CD

,/

a.

Axis

~

___

1.

~

center

/"

are stability the

coefficients, and /~ Cl'7

m Figure

~w

fram C w /C: wind force and angles CP, aced af of s

~

m disp l C

Cy~®-,-

~

Notes:

CA

arraw arigins

/

been __ directions

",\,0/

coefficients, ted by

L

Cy have

,'*0

C J)

clarity, ica gravity nd Positive i Far moment axes of 2.

y/

w ....

REPRODUCIBILITY OF THE ORIGINAL PAGE IS POOR Rudder and Speed Brake Deflections

:~

(-) or

'"

t

oeL-oeR = oa oeL+oe R oe (+) oe

Aileron & Elevon Deflections

--

_~~BF

---/-+ Body Flap Deflections b. Sign Convention :for Control Surfaces Figure 1. Axis Systems and Sign Conventions

J

._ .- .. ~.- .~""'---'- _

n

V)

~~

~ s:l

o '" ~1!

~$

.f.!~

~.-l , ~ 'dl~

~CIi

~~

.....

•

"" 01

------ I I ,..:--=~ L ____ _ , -.-.--.-.---

, , ttI>B2 +--If---I--- b. Model Base Pressure Instrumentation Figure 2. Model sketches

t

I

~~c~

r- ""' =' $.208 x.= .SO

x. 47.79

XJ:. ~2. 12 0

I' - :::::::::-C ___ D .x· ;4B.~

-.

110s, I

\

..

c. Sign Convention for I.&nding Gear Figure 2. Model sketches

REPRODUCIBILITY OF '£HE ORIGU'lAL PAGE IS POOR /./54-

t

~----IL ...

171- 115' '17~ -- . --. ",

N-' ,,-IS

+

~--, IJI!!r- 1140- /OJ!. ~ , "./17 B 0119 1.R1J

~~

k

IQ3 _ fIt: tl;24- tIts- I~ 1"l3 • d. L. H. llIG Door Pressure Instrumentation Figure 2. Model sketches

.]

- ... _--_.n-I!E /I.r:r--- ..... _

• .30/ • .3QZ e. L. H. MLG Door Pressure Instrumetntatioil Figure 2. Model sketches

I

~~J

1 . "-~-.--

\ I

I

I I I , / . , f. L. H. MLG Strut Pressure Instrumentation Figure 2. Model sketches ?l.iPRODUCIBlLrlY OF 1'1-11 ,."UGINAL PAGE IS POOR

-- (~);=i~~(f)~ ) r Mit

m@11

~:'II¥ i

I I ! I :1: I I I I -- - - :, - , -r ' I I -. - -'I" ; I , , I I I I 1---&.3-.

'.

;&wE: ~ mAIN tjl./U!. 0.7/<:.:/"'" kWn£ M ;£)0":;:£ t}i/k; ':::'71<~!l7" g. Typical Landing Gear Strut Strain Gage Instrumentation Figure 2. Model sketches

;' J\

\ / '.;.

(-;~ 0@

) r

~ (3;)).

'T

h

_______ ctl?o/£i

I I I

I~

I I I I I II

I

•

I ·75" I . -I

~ ~I: -

I I I I I II I

I

I I I j I ~~...r.

;\

o

h. Typical landing Gear Door Strain Gage Instrumentation Figure 2. Model sketches

a. NAAL Installati on, Front View, Model Configurati on B68Cl2G20Ml6N28W1 27E55F1OV8R5X9 Figure 3. Model photographs • •. ~ ,<- • b.

NAAL Ins tallatio n, Rear view, Model Configurati on B68Cl2G2OMl6W28Wl27E55F1OV8R5X9 Figure 3. Model photographs

" , ~ '.

... .. -,.. : - - " , . -- .

-

c. NAAL Installation, Bottom View, Model Configuration B68C12G20Ml6N28W127E55F10V8R5X9 v d. Nose Landing Gear, eN ; lO ~v , ~N ; 66 Figure 3. Model photographs

, .

•

•

-(~ , ) e. Main Landing Gear, ~ ; 35°, ~M ; 88° Figure 3 . Model photogr aphs f . NAAL Installation , Side View , Model Configuration B68C12G20Ml6N28vQ27E55FlOV8R5X9 + 40 ' x 80 ' Strut Simulation Figure 3 . Model photographs (Reverse of this peEe is blank . )

il·'

- .... -~ DATA FIGURES 1: :.--- - .... - --.---- ~ ------

.

.. :: :' '; 'T : : :. 1

:: xa YO za ..

• FT.

. . . .

:..,

'. .:: J:: 2D

c "

:s :' .

:::" ... ..

,::,. : .;., I INCHES INCHES IN. IN. IN.

SO.

... . , .

.• .. ..

, :: . . .

. .

.. 19 .., .. :.

... ,. . .... :: ...

.

..... .: :" "': ORHATION I . ..

.. .. .

NF . : : I .:::::' .,,' '.:: :: . 0405 .0000 1 .. .. , PAGE .. ..

.:: ,'.:.

:' ", ....." .,,' . ... . : . :::: 474.8100 375.0000 936.6800 1076.7000 ".: " 2690.0000 •• .••.

' ::

••

:' :::: ... '" :.: :.:: : .. .. ': . : ::: ...

•. .... :: :.,:";. .. "'. ':':':::'

: •

:.': .• :

:': :::: ,.:: :'. "

1 .

REFERENCE ······· .

: ••••••• .

MRP ' : . ;: ....

X YHRP ':.

SREF LREF 8REF ZMRP SCALE

'''''I ~ 1

:: ...........

•• :: . :. . ... ":,, "":'

.:: ••..•

'" •• •• ' ...... :: • •••• .: ••• '.

. .

......

• ........ .• •. .. :: ..

.::: I , . . . . ': " ...

.. :.' :' "': . :" .".... ", > 1 '.. ::: I ' I 1 · 1 ;:: .:: ,.

..

.......

.. : . ' : •. : .... .::" ... :•.:: " , ...... .•

: •••••• :: .. ... .... .... ., 1 I .," :':' ......... . r ::

''' 1'" •••.•

: ": •• .. " : ::.

::: .... .... ···· ,,::

1 ,1 1: 11 L:' I

:11 · 11 .

..

"" :: 1.

: ': . . : ,'

.•••.•••.••••.•• .•••••••

:.', '. ... : : : .. ' :.

I ........

••

' .. ...

:.~······ :" ::: ••.•. . :.

I 'i 18-t I 1'

'

' ::: ."." 1

II :1

ft

': •••• : ::: : :: ''''1':, ::: "" "" :: I'" 1 1 .. .

· 1 :

1'

.. : :.· " '::

':.' "': ·. .. ""I ......... < .,,'

(II , I 0 :. ":":;. ······· '" .:;:

'••• ".:.,:::: ." "" , ..... ... .... .."

1 V

vI 11 " •

..

'. .. ..

,.,

. ,., .: . ..•••.•••

.,., "" .. ., "

< I

I ~/ :.

•• • .' ..........

,., : ': ." .... '''. ',:: .".

:~

~~ I '

COEFFICIENTS :

~

••••• ' .. : ....

.•

' "" "', '" ' :: .... "" ;:: ,:: .,,'

<'

L I

I 8 . '.;; ••• ..: 1 ......... , <" : .. .•.• L ".' ......... :;:- "" •• ....

11'1'1 I: ...

.

" ..•• " :: ,' ~······ ••. ....... ::., ..

Y:V I

1 1 ' 1' I' F . 1: I : 1 : 1

.000 .000 .000 T, ' "to ,", :J ",·, "': •.... •••••••. .: : ...

.:" -·> l'.OOO ~', ~ ~ 11.

, :1 .

: ... :, ::

•••• "" ". ·· :: . :> ·"· ••·'

. .......

1 I I , j ' I

[ , T'i' +:: "":" :', ' k

':' ,:: ". ... ~: .::: ~

i i AERODYNAMIC ·· : ,' :f ....

~ :

•••••••

' ' .T •• ....

OBRK 1" ~t-;I I

II'

'::' ' 5

~ '.

, ·· 16N2e'rl127E55F 10 'IeR5X9 VALUES THETAN THETAM ELEVON S ••• ::. -:: .:: ·:.::

.: . f :,.'1 ,T ." ."

k tIT1 : ...

:

, ., ,·

•• :'.

":' ..

' .,· :'..

f'~L 1 , .

'* , :: ::,:';: 00 2

1 i I I""" 1"1 1

1 1 ·: .169 . 000 .0 ,

12G20M ': . ::": "',<

1.190 '·' '.' .•. ''''I:,: PARAMETRIC ~ .'+ ...

' ,.

.:

eC "'F " r

•• :" ··.': I f-..; 1.

II ~ ..................

· , ..

86 . LONGITUDINAL

::-, ":'*" , ".

r , . -I ,r c,I;::;I- •• · . '. ,. ". ' . . .......

. ·

.:'.':' .

)-'p.- / L , "',' •..••.••• ,. . ' .. 04 ',:, '.•..•.

MACH BO'LAP PHI-N PHI-H RN Ir k l -'t . L .. :- ... : •..

. '

LlPt

OA . ...

"' .•.

f-,-' 00 00 o FIG.

J 4 . 000 c " .0 .000 ~2 A 5.0 '0.000 BETA -5 039~;:' -10 0471 v46 04 n u~u 037 035

-- .03

· 0481 . • • • 044 .043-~1 .041":": • • .038 . • 036 .

, OOI ) OL B

~

<---- AFF ~ ( SYM u

.

kO YO ZO INCHES INCHES IN.

SO. FT. IN. IN.

I.- r1"::1

JJd

" ~ .

~.

.,."AfION .

>

fr

: ·

1....

" : .0000

•• PAGE

474.8100 936.6800 375.0000

'

·1

2690.0000 1076.7000

<

l'r

rr

ii ::

rF •••••

~ 1:1

.r .

: REFERENCE

" ~!

r

.1

SREF LREF 8REF XHRP YHRP ZHRP ..............

................. " =

" ' <:

••

q

rr ·' Y'Y'Y"I"'f'Y: )

YYll ..

: :: ..

'.

Y . ........

" ' r :::~ .....

.........

.

..• l

rr <

:

. ·IH·I

"

., 'H

·

l :

' r:r r.rrrrl

: r ... > : ·' n ;~ .I .

l ;:

111'111111111 ........ YLIYl I

·

:'"

'.

I

l' r :r 'Y:

J rl'

•. ''

:

..... :: ••

I' I ..

f:r; ': "· ; :~~~~; : l 1"l YI .........................

" :· .

n •••

lrllirf 'I"

rY

" : :·

r I:I

rllllllill

< 1

.•••••..• ·' Y:r L

.

:: : ·

........

rr

111fT

l' I a ' .

'

;;~; ........

"'" r ·' ....... ::: .. 'l 'Y: \,NT

If

P.

••••••

' ··

~;:: \\\\ ll

'.'

l' COEFFICIENTS

:.' '· •

•••.

:~:~

III!!

Illf

l Y'

•.•. •

"' :: :;.: I

IT)$t-~

' .,.... :: "" __ ........... 'l : .000 .000 .000 I , 'Tl.

- ''I ~:: 15.000 "" .... ' •. p.

III l

> 1 ; p __ , ••• ~ "' l 1 IIII'i~\:I\;~\:1b " ~J'ktlLYl ' .

•••...•.••..

... ::' ,

. ···

....

l l · " "1' . AERODYNAMIC

'

" ..

q

1' VALUES I. I SPOBRI( THETAN '1" ELEVON THETAH ••• ~:~ '· : ••.

.•..

f$~llir :

111 r

'

'

~ : '

IIIII ._._

1"1" lltl ..

: 1P;~:.l • 00 '" .

· ::: .169 .000 .000 .000 I

llq

••.. •

1.190

:- :,}::KIT

" ,· ..

PARAHETRIC ......... .

'''1

III I

. 1

lq

: ll

.

... .•

q

B68CI2G20MI6N28WI27ESSFIOV8RSX9 '1"" .

....

.

''' .... LONGITUDINAL

III

ll

••• ....

1"'I"l "I " f .

HACH .•..

80FLAP PHI-N PHt-H RN/L "' ·· , I

mlll

· :.,. ... ....

OAI63 ::>: LlrJI

,"

.. "1-' I I Ilq

r:I Iq

..

. •• '11.1

' 00

q

I ' 'I 'l I

ttffttltJrlrrrrrrrl 1 I

tlmt

.000 FIG.

5. 000 BETA -5.000 10.000 -10.000

.030tl .025 •

• .010 -.

-.010 -. -.0201

~

...

(AFFOOI) SYMBOL < u

. .

, ' '" ", ... .

XO ya ZO ': ... .. ;::. ." :.:: .. .. ' .. ': ,," :[1 :: : FT.

, ..

,

c

4 ~~ .. .. 20

..

.. H ' .,~ " .. ::, ii: ", ::: .....

,. :::: •• ,., .. ,~

INCI€S INCI€S IN. IN. IN.

SO.

~ : , '" " ' .

.. ~'" ., ••• 0:" ::::

.,, :,:1 :::: iii!

• ~ .... ,,," :, ,"

" " :: :: .. ,,:.'

•• .......

:::: 0:0: 0:0: ............... ' ". ::" ::: """."

.,~.~ 0100 0000 """ ..

.~~.'" ,,0: ~ "'" .0:, .::: !m ::::: :'."

INFClAMATIaN _ .040~ ....

.

....... PAGE ••• •••••• : ...... .....................

, "

iii

.~ .... ... ,':' " . ::: :::: ;.,,:,'

.::::::: :';.

474 936.6800 3".0000 I L : 1076.7000 > ,0:0: : 2690.0000 · ..

~ ::;,, :: :: ~

.

·

. '.':: .. ',0: ......... .~ 0: ,' i[ ••

I " : ":' ,." "" :';.

, " ...

0:" '" :::.:;; ..... .::' ••• "0: .",.:.:,::,:,'.:'., 0:0: :; '.:::: REFERENCE : :, , ,

•.......•.••.••.•••••

•• ... :: ' ":.: : :: "". •••••• •• ••

~

YHQP •• .::::: .·~:~' .'.' ,':: '

$REF lREF OREF XMRP ZMRP SCALE I ,, •• ' ... .

'.:" :: .............. .... ~ " " I::,' .,,' :i:; ~ , ' " : • . ~ • .

" ,

·'

::: :;::: :~~ 0:0:.' ' ::::::. '. • :: !!: ,.

r

IS

:; :::'

.... ·.

, "." '''::::' i:j ••• ••

•

I : : , , ........

." '.

0:,' 'A ... ,.0: .:.: 0: II •.

:, :::.~,:.

'~ ••••• ...... 0:: , " ,0:

"" ;'

',': ',~, :::'

! I 1

I'...· I

r •.

+ '.'

, :::

.:. .:.: ' .... :: •• :~' "" ,,0:0:, ·:!;j!:i :::'

,:, ,

.." .... .. .0:'

., • ,;' :'.' .~o::: ... •••, 0:' i:: .:: 1·', " J:.

0: "'" ,:.

0:' 0:::'

~ '," :,. ,., ••••

..:' : i~ • """""""

' , ' ::".:1 •.••

:.' "~' "" '0:, ......

:..

' ....•................•...•.

••••• '' 0:,' ::~, :.'.. .... .'0:' ::.. :,:: ..

.····

I I

.,..

II ' , : :,: ... " ::: :: .. :: . :.: '.~'. ....

.., ~::. : ....••• •••• ':: 0:0: :.~ ,.~ .:::!:; I j

. +

•• •.. .• ~ ~' ..

'::

".' .;' .: .~ •..• "

Q ~ H ''' ..

. .~' ,,: ~~: ':::.'.;: ..... ~'~~ ,: , ~~ I k' .

~ .• 0: ......

::::- " 0:. . . ; 1••••••

• . ,,'

Id??

' 9 .... ,'",.

'" : ' , ....... ' 0:' ••.

.,.., ':. ' .'" ' .

COEFFICIENTS ., ~': OV8RSX9 .• " ':: •••... ,,~ ' F I " 1 1: I ,I . ,': .

,.

•.•• ,... / :';,- '., .• 0:.

• ••••• ,.~. :0:, 1 1

.000 .000 .000 1

'... • '" "" '.', ',',"' "" .

1~.000 ,.

.j1W

• ' , • •• , ". ••.

.".'

f4 I I : ',. ' l" .• •• .. , •• .'

AERODYNAMIC , " ' ., 0: ••.••

••••• ' ~" :. "

1 : •• .•••••.•• VALUES ELEvO' SPOBRK THETA.... THETAM ... 0:. ..

..••.

" "', ' '0: " 1 1 · •.

C I .

" 1 , ••. ' '.:" .. '.,.: . 0:. .• ." "': ,..

.:..

••

~ . •

•• 8 ..

,,0:,' .0:, I 1 1 , .000 •• " I ,.

.169 .080 .000 '" 1.190 ,~" ." ", . > ~ ' PARAMETRI •• ", ••• ."'; • ' I l '.,"" ..••• : ~' B68CI2G20MI6N28WI27ESSFI LONGITUDINAL ". 1 ••••• , .,:,: ' I ' I ' I .

' ,. ••

,.::l....' • ••• ':, 0: A~i

, ' '. ...

'" , .

MACH BOFLAP PHI-N PHI-H RN/L ••

.'

I- OAI63 ",':, ,1 ".

"I

o FIG.

.000 s.ooo 'u IS 10 10, BETA -S.OOO 10.000

I) ,os!

,45 ,35 .60 .55 -10.000

~

z u (AFFOO SVMBOL

~ Ii!

• .

~

.

,, :; ... ..

xo ZO

'0 m' "

":: ,::, FT.

.

.. " . ."

c

,." • :: ' ....

INCHES IN. IN. IN.

INCI€S so. 22 .• ::. ' ".

:,', :: ':' ,',' """"

L

.: ': "":;; .'

;; " ' .::, ::,' '''' ,.,.'.:::. ''', '"

p 1 r ··::·'!; , .

,· 'L :.: ' 1 ' :1

.. , ••••••••••

INI'ORIIATIIIN :.;: ... ,',I " ••• ,,' : "., "" ........ ";; .0000 .0405 RIC!

,. ' i

I PAGE ::

·· ;'

:: ..... : ,.

'::,. .... ,,,. "" :::: 474.8100 936.6Boo :;75.0000 I 1 2690.0000 1076.7000 ':;: .1 . ,

' 1 ·r "8

..

"" . "" ", :::

," ·" :.:::".,.: :i':::'

r"""

'.: 1:" 1.·· I 1

' ., . :'.: :.;; ::' .. , " '''. ::' · i ",',' .. :::: I '····1 REFERENCE ••

.• '.'

"

:, " .:

',,:;; :: ", : .. .•••• , ::: :::' "'

SR'EF LREF BREF xHRP ,HRP ZHRP SCALE V I I': , > ': 11': :. ,.

~ !':

!

'>'1.,:' .... .... : : .::. , ,','::' .,,: :.:: r I: '.

", ' •• .• ".' .: ... • : : ,., •• '.: ::;; •• :::: "i r " U .

:.I. :: '" '" , "., : :

c II 1": I "

1"1 ' • .

"', ,. .' ................... ,":'

:: ;;',;:,; :: k ,,: ' .... :. ::·::: ••• ,:: . • .,' .,,' :: ,'" :.," "" :::: t:::

' " I I

.'

..

" "" •• ,.

"' , ,."F ""

I": L •• :: .

•••••

:' .. •. '"

'.' ... • : • :.:. •.••••. "" .... -:: ,::. , :' j 1'1: .. :" •.

". .. ,.

.' : : , ,';; " " 1; , ' . •. : ' ,,.: ., , .

" .. · F '::. . ... • : : • .,. ::., :'..

, '.' " : ::" ""

." ., . ",,·'.:: "

, , ""

II

:::: ':" ,.. ••. ......... ::: ... : :::: :,: ""III L" , ' . . ., ., • ,: .. :: :: " ..........

a

11 : i

.

.

..

:: .'" '" ... ... ..

. ,::: ' [;.;.lIJ ,':. 1 ..

' ·· • :

.: .. : ':· ;':-

",..

' :: ' I ' J ,., ., :: ..

' v ... • '::::. .. ':' ..

:,', 1 ' ...-. COEFFICIENTS ......

. .. , .. :: .: ,,,,,,, ,' ...

IOV8R5X9

:,'1

L ....••.• • : '' :: ::1 ""' ···· ; 1' ' , ... ". '

... , "" ...... .' •••

.000 .000 .000 ': "" ,,:: .". • 15.000 ' , I I!

,I :: 127E55F . ' •' "' : ' , , ,11 :: ,. ,: ~ •• I • AEROOYNAMIC 1 .

RK ".

.··· ". .

.':: ETAK I I I ' 1' ..

VALUES THETAN ELEvON SPOB TH ': , ,' ',: " ...

: 1' •. ..

: -1-

.. ..

• • ",.1 "'1' ... :': ~,-

,' ' 1

•.•

",' ." ":, I:"~ 1;;1 , I .169 .000 .000 .000 ,. ..... ......

1.190 '. .. :'

PARAMETRIC liil

.

..

.... , ,: "' ...

re ,.:: I I, .

BSBe 12G20M ISN28W .. '.

LONGITUOINAL "' ",. :.: ",' [ F , ..

.. ..

• " ,',' . ..

' ,.

. , HACH BOFLAP PHI-N PHI-K RN/L • IS3 11 " I .

J j • :' 11 .1 OA : " !

...

' .,... . .

.-l-- I 1 FIG.

'1 'I .000 5.0~0 BETA -5.000 10.CJO I ) -10.000 UL4,l 020 014 008 .026 . .022" • .018 .016 • .012' .010 -.0021

~

~ AFFOO

J

( SYMBOL

: . '

••

~ .. " :, :: m :'1

• 5 :: ::: XO yo lO

:.,. ~:~: -::: '::~ ,: "J .... ' : : .~

:::: .::, ::', :::: :: . " .: .::: FT.

.. .• .. -

c

' ;: ,; :: 20 ::.

.:: ·;:: ":' :,: ::" '::' ... ::. ,::: :::: .:"::.: ':: INCt€S noct€s I~.

SO. IN. IN. 1 k ": · 1 .. , : . , " " ,V ' .. .... .

"1:: ::' .• ':', ,,,. '::' ,.': . '::, ::; :' ., :':,': ' ..

...

.· : :' •. , :, .. ... :: :;, :.: :i ':, .. .::.' .,:' ::::::,: ,:,' :'" : '. .... ... "::' :: ,", .::: ;'. :;::.

.. ·

.. : ': •••

...

68oo :: ::: .. •.

IWORIIATltlN : ::: ·'· ::" ... . :: "'. ':,' -;' :.,:': .. .... ": :: :: :', :', .0000 .0405

n+ 1

•. ;" : PAGE . :: .. '.

i

.. '. ••

.: ::. :" ',': 1 ,": :::, ,'i' '::' ,.:. ':,: 474.8100 g' 375.0000 2690.0000 1076. 7000 : • ...

' : : : •..

... •• .,..

.:: :::':: '::: ":: :::, :::: .:' .... , ;, :~ :: , ::" , r r : I :.

:·

,' ':'"

:~' :.:' ·:' ".,.: ::,. ",. ::: :::: - :::, REFERENCE •• '1 ,:~. : .

". ::::, ',' .::':; ., '::'" ............... ':, ::~. :~.

SR£F LREF RRr< _ XHRP YHRP lHRP SCALE ::" ,::: '::,' ",; .: ..... ............................ -7 . ::;;" ..• , ..... " :: . .....

.. :: ...

. ::,. ~ " ::. , :: : " '1" "': ....... ' ':", :, ... . " -:,,'

, ... '::' ,': :~ :::. :::: ,:: :.::,~ :::: :'

, " " , IS .. " ,:::.

". "' ",:::::; ,~'. ': _. .;;, , .. :,' " :' : :' ::; .. :: ". .. : .:' . '~'" :::: '::.: "~' ::: : : ::, 1 , I 1: " :1: ' I .: ,.

'Y :

:.',: .,. ,. .. . ::'

,,~ '> •..• " · :~'" .' : .~:: :: ::::. :':. ..... "., :::.'~. :"' ",. :: ",.

'r 1 I ...... ''';; : :,.', ..

:: ::'" '~ ::: "", .::: :,' '" "" .:'.

I I: J .

, : :;'1'"

.:": ,:' .'

L' :" '., :: ~"" :·.· :" :,.::':: "..., .'" "" ,.:.':'" : .

~ 1 , ,,;: ,::: " :. '~ ":· :: " :" ': ':' . j ·· :: ': ': ,:: .• ; ..

' '. ••• ,, · · . ': .':: a 1 ,, r::

•• .. ,,': ,'"

:', •.

., '

., ..::' ".

V V' , " ":.

"' . : : .

. 9 ".

~ :, ,.'. : " . ,: ,.

"" "", COEFFICIENTS ' '::', . k •. ' ,'.

...

::', '" .-;:, lr :":"

i: "

;~I~,/ ::· ...(iY ,,, ,'" ":., I 1 I ' 1 ! . '.,:.: . , , .. .. .

:":: " p

v .000 .000 .000 7 .. ..

':} :', '.: .....

,. ,", ,., ,:,',.,: '· ' 15.000 ..- i >: , : • .....

,. , -14 ;:.······ ,, :: :.'

"" .

.• k "" I'-: +-1 6 ... :1' ..

.

. . ,. :: , -:- < AERODYNAMIC ....•. . ..

+ ., ., ::'. "',. ',: :::':' ''' e- I:: ': .

VALUES THETA" THETAI1 ELEVON SPOBR" .. ," . ......

I_'~ """ ", t- ..

,.

" ': ." .. .. .

:'.' ','. ."

, I ' .: ",., ......

.169 .000 .260 . .' . "" .': .• ::, 1.190 PARAHETRIC , I :. " -+-+-+-H- ..

,: t-t--

68CI2G20MI6N28WI27E55FIOlf8R5X9 1 : .

+ , B : ,'.

LONGITUOINAL :::.f::: .,., -.,.

.

..

' ;, ."

, I , : lH / L +-;,:.-1 .....

HI· BorLAP .'.

MA PHI - N P RN

~t--

'" -_ + ' ,,-- -.

C

0.40163 -1 ' ·· " ,.:

_~

- 1 1 1 1 . ' FIG.

.t

.000 7 5.000 BETA -5.000 10.000 -10.000 04 046' 045 04 043 042', 041,1 03 038 UJ/ 03611- 035 03

~

.A < ( AFF002) ~YH80l U

' '

~

] . :: .:;1 ,-: ;:· ... •• :. : ya ZO XO ' :. :::: :: . • .

FT. 1

i:::

: ~ ,. :,: , 20

:,:: .

;::l=" ::: :: .:: .. :;: ..,

IN. INCMES INCI€S IN. IN. F

SO.

: • . •• , 1 : ...

:"' .

I ' L

. :: ... ::: ,i:: :....

:::: .::: ..

'

.. . ':.:':. ...

.•• ::: ::.

INFGlm"ION ., .. ,:':: ... :.: ',.: ": :: ': ..........

.040' .0000 ..

... : . PAGE

.. Y 'I

:: .. ::

"" :.. :::. ::. "

37'.0000 474.8100 936.6900 \076.7000

26!O.oooo : ::: :'::::' .••.. ••

..

. : i::! ... : . -

.. ::. :::' :"; I!: r"" .

:1 .. .....

::. ':'.. :: ::: ::: : '" ...

:':' . :::' :;:: ...

!

REFERENCE .. ..

. •. : "

HAP :::' ::: .::. .• .: :: .:.

I""P SCALE SREF LREF 8REF X..... v :: .....

• ......

: , :: :. ::: ...... : 1 > .. ": '::. ..

:j: r 1

.

.. ... ......

•.. : :.

:: :: : •.. - :: ::,: ..

I. I, !

V :. ..

.

... ' . ,.

.... ." ,.: j-:- ' :: . ...

:: :: ..• .:. .: , ,:::: .:: ..

:: .. .....

:" " ,,; : :: :, . :. ..

....

I ,:: " ' •• .'" : ::: I I ":::

LLL.!

:.: ..... :: , ::.

, : ...

~r- r:'

1' L

.• .

, . ..

' .',,,, ,...

;:.: ... .• ....

l :': ".

'.. , ':':::':':':;:',':;";';:::,:':: :: .:.::

I>I

.

::;.

': ·' 1

•• .. 'I

:: ::, :":. :.. :

••

: ..

.....

. !i:.; .. ............

:. ...

'.:: a

j IV

'1 :: :. ,., .......

:::' ':. ~

10 1·'·

'\

.

'\ :...

::. ::: .. ...

r\\\ '" 1,\

II

.

:: ;::::::: ·':

." •..•

,,\

I COEFFICIENTS

\ ......

::' .... •••

....·

~I\. \l\

I lit ::: : .

' ~ : .

'\ :.::.:: . ;:: '.: ~.\ .

!'\:

~

. •.. .: ..

.:.

I\, 1,\ I~ ,000 ,000 .000 7 ;:. 'b, .:;: 15.000

~

~

..

, I'::

t-' I I

:' '

:.:.

AERODYNAMIC ~ ETAH

1 11 N

S VALUES ELEvON SPOBRK THETAN TH ,::.;:' .

," l

:': 1

:.:. '::.

I". I" I I .

~ 4

., ..

.: 60 ':"' : .........

: r-, LJ~ , I I

AMETRIC COO r:-f- "

1'-..1 .169 • . 2 .230 1 " .

R 1

1. 190 .

I........ ~ 11

PA I>.. 11F11

,1 :1'

I -r

., :': ..

'" I ; 1 I II 1 -r B68C12G20M16N28W127ESSF10V8RSX9 LONGITUDINAL ::: .:.:: •• I I

I 1 I I I 1

•

: - ~ M~ I I I I I HACH BOF"lAP PHI-N PHI-H "NIL ,,:: ,;:: ... - .

11 I 1 1 1 I. ! IT I I I

I 1 I :1 11

::.

""

I I I I : 1 I I I

0"163 I 1 I I 1 I

I

FIG.

'r 000 000 ' I •1 .

. .000 . : 01 5 0 1

) 5.000 10.000 9ETA -5 " -10

04(1 035 030 0251 "")" 010T 00 00 01 OIS~' 020 030 02

~ ~

.....

LI ...

< ("FF002 S'I'H9Ol..

u

. ' . , .

yo :.' 7 1(1' 20 :::: ;::: ".: I::: . :.:: :::' ~:: :,,' :: ....

" .. ii ,: :: .. , 20

;::: ii:: 00

i::l ;',' ',,: : : : ; · '

INCHES INCHES IN. IN. IN.

SO.FT.

..

:: ••

:;:: .. j:il .::: i

,:,:,:,. ,,:: ""

I

.. : •..• ..,:.;: ;.

,':: iiii::: ,,::

ill: :: .: ""

INFaRI1ATlaN ;::: ji·! ::;~ '::: ••

.0000 .0000 .0405 :i: ;" ii!: :',' :.,: ••.••• PAGE

:. 18

..

:: iii: :.: "" ':' .. .::, ,':.

936.6900 474.8100 375.0000 ;' I : 1ll76.1000 : ...............

.::: li:1 ill '::, ::' :,.,

iii!

........ .............

.• •••••• '

i!

...

,,':

":: ·111 ... !i ,,' :': :., ·i:· ':,,::" :."

: ':;'::: REFERENCE .: :: il:

:.!

SREF 9REF XHRP YHRP ZHRP .... .... ~':' ' ::: ,' ':"

lREF SCALE

i

," .................................. ;::: ::::' :: '::: •...• :::~ ;::;. .::: ::" .

•• :.

:: !:: •• •. . i:·ii

...

::,' ' "" I

I

•• • .

' ..........................................

.::: ,::: .'

..•••• ''.> .....

'.,.

:::: .... ••.•• ·~· '::::.

:: .:, ...'

: : 1'1' .1-' ...

:::::: : •... ... •..• .':: ,," 1.

1 1 ..

:: : ' ' ;": : ::: "': ..

:..:>

': :,"" ": :,,' •.

. '" ••

': •.

:: : "; ., ..

•..•.

, .... :::: . :.: '::: ,,~, 1 Iii:iiii : .:: :':: ~~~ ~~:: :~~'

.... •••.••

'

'1 ···

::: ..

•• ~,~~ 00:

;: .... ·· .···,,·

~ I.

:. •• :', . ..

.

,~ ... •.

i •.•••

..

•••.•••••. y II .• ' '.: i:: .... ,::~ .. .

!::

. •••••••

~ ., .: :',

........... ,"" .... ....: :::, .'

ex . .

•••• ~ .:'.

•••• ,~:, ,::, ..

, il

... .. ••••••••••••

:.., :::,

. ',~, ,:::1"".. '''' .<

:.' ,: ..•• ::: ,,:,

~~t

COEFFICIENTS .••..••• , :.

·i: ':'-:~: •••• ':, :',: '1 t'G~ : 8 .•••• ..·~.·. ' •. ...

.:.• •••....•...•••.•••...

• ' ,~,: ••••.

" •

.• ~"

·

,'.:

:, •••...• •..•

.• :i: ~

, L:..:.: , ..

.000 .000 .000 . 7 ...

.'.

::.: ..... ..... ':', "', ....

25.000

~

.

' ..

j: , .. ~ I 27E55F IOV8R5X9

," '

.•

.:: :~~~ ::', :.': ,

•••

. •.•....•.

... .. ~

.•

:::: ',.:

..... ." ....••

AERODYNAMIC ......

•••• ~ ~, "" ' .

• .'

16N28W VALUES THETA.N THETAH SpoS'ltl ELEVON :: ..

..., :" ::~:' ,':' !

~

..

..•. ... •• .

'

:}:: : :~:' ~ •...

' .: :: ,'" ···· '::, '~~~ ". ••..

:

.! . I

!

.000 .169 .260 .230 ..

12G2DM ': •••••• .

1.190 .".

.•..

.. : PARAHETRIC '.

'::. ii;· :"' .... .... ..

••.• ,',' ••••..•.....•.•.••.••.....

~ ,: .

..

;. .

868C :': LONGITUDINAL •. ~~,: :',::' .. ::;: :.:. .•.. ..~ 1' 1

•..••••• 2

: ,-~

;::: ... ::,. :'~' •.••

~ .. .

,' ..

: " ,:: : .

BorLAP HACH PHI-N RN/L D4 PH1-H .::: ... .

.••••••

, ••. •.• ~.: :: ...

i·

, .... •. ..

OA .:::; , .. ..

•.

•••. ...... ::~, . ,,',

; ~

FIG.

.oeo 5.000

15~ 10

~~ ...>v 20 ',,' '

BETA 10.000 -5.000 .55, • -10.000 ·:: ' · .25 • ::: -.05 -.

~

~ z r-; u ( AFFDD2) SYHBOL

: .

••

. :1 •. J

m .,• : 1(0 TO ZO :: ." ....

.

, " .••• •....

. 20 ':: :: ":' ~ .·.m .•• ":' 1.

t •

INCI€S INCI€5 1" IN. IN. 1 50.FT.

• .: ....

,, " .,,' .: :' :::;::

... ., ·" '::.: ....•.... :::·

I

••

,:,' · I 9

:.

". •• : ............ , .i::. ..••••.•. •.

·1·'· ·E .

, i.·.: .

0000 •• .....

::

·.· .•

I"'_TII'" :,1':,.: ...... ' , ....

.0000 .0405

••.• PAGE

. : :.: i: •.

.', ...... :.:.:: , 474.9100 936.6800 375.0000 I:: "1 1.

' .,:, I, 1016.7000 2690. r . . .

•..

:. :.': '

:'

!. : C:·:·. .

::" > ... ....:: :.

.

.. •• .: ': •• ..

.:'1' "" : :.

R[FER[NC£ :.·. :. ·" :' : :.:'.:.

••...

"L' .•••

",' .:. .,. : '

....

THRP :: '" :.

SREF LREF BREF )(HRP ZMRP SCALE L , :E' : .: 1 ·· ..•• :..

: : ,·:.i· :

.."., •...•. •••

••• ';: ':' :: : .' : .:: ••.•. :" ... :.' "-" :. : ,. 1

I

~

, .: ••

. •. ,. P

'1'0&'1 ., ": !: .i·: ••• •.. : :i::' THE :: >1

!:: ••

•... ()f)

F

.• ··

POOR , . ... !:!:

'm ... '''l:: ':: .• :•

L " P 0 , I' p:

' ••••.•

': OF .. .• : : .': IS : . ,. .' •.

I IS L , : ..•.. . '.:::: •. ···: .: " . : ,., •.•••

·

' :': ••.. : .• ,..

•• :: .. :: I J : .

: PAGE [.

i.·.!:,:· :':

:. ', ' " :i.:, :•:: PAGE

: . . • ' '.'

. ••.••.

••

'.' ••••...•.••••.•••.•• ..•• :'

1 I

:. "

.: '·,'" : :: .:.

, 1 I II J .1 .... ' • .l\t :: .:!:. .: :.

. ·:·'''·

'1 RT"INAL

1 ••

EPRontJCtBILITY RiGtNAL .

.. .:: , :: :'

REPRODUCffiILITV " "\ " ... .. ... ': ::'; Cl , ' j! iJ ·

'1 I 0

:.: < [, :,:: .. . .... ."j' V' 1 1 ~.

,.I

.

;'

'1

....

•• ..... . ... ::'

'."

.": ~ ::: '.': ,.. .': v

' . COEFFICIENTS

I

.: ,.

."

::: :".. ". .:: ..

1: . •" : : .

.• ',":" ,.:, ."'.'

: :.'

1 I

•• "' ,

.••

.

·· I : 1: .000 .000 .000 . " 1 ' .......... ...

.

,:. ,. .... •

15.000 ~'\ "~ 127ESSF IOV8RSX9 .

.. . .... : .:.; is!'.

~ 11M

':

'

,' .:

••

:: ':' .••. ,'"

:

j- I 1 8'

AERODYNAMIC TAN TAM ' 1 ".

... ,••• II

.'

16N28W VALuES THE THE ELEVON SPOBRK · t :•.

, :::, ~t: I : : 1.,

'" :., .•

•• ",.

J ....

,. , .

•••.

':,

60 .. '"

,: : .,., 2G20M .. ': .169 .000 . 2 .230 ...

'

...

1.190

'.,. '" ••

PARAMETRIC '

1'

..

' " ':" .:.

,.

B68C 1 LONGITUDINAL •• .

I

1" .. : . .

: .. 04

," .......... ....•

HACH BOFLAP PHi-N PHI-H RNIL ....' ,·· "'

163 'I' I

•• .

.... ···

~ I 10- OA : : . ..

•.

:

L

1, FIG.

. 000 .000 o 5.000 I 0 .

BETA 10.000 -5 -10.000 024: 022 018 008 002 .026 • • • .0 • .006" • 004 • .016 .014 .012

~

E AFF002) u ( SYHBOL

i

: ,I:

~

III

:.

:, PAGE 'i'..

;i 17

,},

\'

.

';:

11111 11111

::

,"

".

:'

o:'

:':!

Ifill

'.

I

r

t

.

a o

\!".'

'.

COEFFICIENTS .000 .000 .000 25.000 AERCOYNAMIC

IIIIllll!ll

TAN

:':".\: :\.'

VALUES THE THETAM ELEVON SPOBR" .169 .000 1.190 i.ooo 2.000

'd'

PARAMETRIC B68CI2G20MI6N28WI27E55FIOV8R5X9 LCNGITUDINAL .:.

.

MACH eOFLAP PHI-N PHI-M RN/L CAI63

11111111I1I

FIG.

.000 5.000 DETA -5.000 10.000

-10.000 :::<

: .

~

..0 ,-..

t--:- < CAFF003) SYMBOL U

. ; ..

. :: •• : ..

XI! YI! ZI!

':" :.: • . ••• ~.

• ..:. 10

;: .

••• 20 .

:: : : ~:: . ' •: ·" ;iii ' ::::: ::: :: .;; :.:: INC~ES INC~S IN. IN. IN. ~

SO.,.f. 1 •

.. .

'.'::

" :; :: •

00 ••• :. ; ..... ::: iii ;; '.: :::: : ': .::;:;.: : 2 : 1 1 L •• ..... :1:' : ••• : .. . ········ :: i': :'.: .:: '::: ;;' ::: :=: ......... .':':: .•.••.• :

::'

I : I ....

: · i: :: ........... •• ::. . ,,, ·· :. •• ; •• •.•.••.

::: ii

l,*tlRllATlIIN :: ::: •••• ••.••• :::: :~: .. •

.0000 .0405

I r r I 1

PAGE ': .• .• 18 ' •• .: : ; " :. ~ ;; :- .

;::: . : .:: :. ::: .": •. :"::" ..

474.8100 936.6Boo 375.0000 2690.0000 1076.7000 .• : :: .

..

: •• =.

.:. :: " I "T :;:. ::: . : :: ; .. :::: ii.: : ::: iii.': lr 1" . ". •• :.; •.. ,{, . . . .

: ~ '; ' : •• . ;.:.:::

•

.:. ':" :;.; .... ": '::: ~.: .. -: ••• .....................

.'.

REFERENCE ••••••••

•• ••

' 1 .. :.

' : X.

: :':;: :; :: :.

:ii: :ii': :' :': T : . . .. i.~:. ; $REF LREF BREF XtalP YHRP ZHRP SCALE , :

.. •• '1'"I •.• 16

• •• ••• · .." :. ii

~.· ;' ; ...•.•.........

'::: •••• ••• .

"; :.;:'; :' '" ::: ·;;" :,: ......... ..... : I , I ~ 1 •• :.

~:::".'" ·· :: ;; ;. : : ,.: :::· :',.

•• ....

.. ;,'; :- ,_.. .. ••• i';: : .,: .;. :::: ': ';i '::," .: .

·::':"i: .':. .....

.:ll ~~

r' I

; . . '1 : .

:•• :' ..

•• ':' •.

.i •• ... ..;::; .• ·" :::: . :: :: I I I I r .

: 14

~;:.: .

:. ;.: ':'I : ..... ••••••• :::: ~:. •• '" .... . .::: "..

, : : : '.

; ..

::."""" •' ':::: .: ::::: :;: :'.

~ " r" 1 . •••• ;. ........ :. .. : .. .• :; jh- ••••..

:'!

.;: :::: :. .... :::: .. .

: : : . •••• :': ..: ····r""···· ': .. ••.

:: .. · .: "' .. :::: ..

.;'.' 12 :. :: . 1' .

_.

::"""

: .:.:: :.:: -:': .'"

~ I:::· •• r . ': ...

.. . . •••••••••..•••

• :: .' :.::.:.. ...... " ................... •• ...

•• .. :::' : :~ .: :: .: 1 :::: :;;.:.:: .;.:. :: : .. •• ......... :,:.;."

••.• .: : ••• i:' .... "; .:.: ,:: .;.: • ; :1 :: " ," : ' : . . ·~'··:::."' ... ...

.:: .. i.·.

0 a : ..

I "' ; ..

\, :: . -: ~ .. ~ i:: ... :::, ••• .i. .. .

~.

: : . ..

i: ::.::: "tIIIYI- •• ·· ; :.: ••• .:.'> .... :: ~\ I'.' I' ~ . 9 ; : . : .

:; :.: ~ . .. •• ;~~ ••• : ...

1'\ ' ~"

COEFFICIENTS ....

: . 1 .. •. .. :: .•• :": : .\ . :,,:: .

lOVSR5X9 ~

I ' 1 ~, ' 8 l~ " . .

..

ii ..

:.i ·.·. ,.:' :': . ~ .... .,,:

....:: ~

~ .

. .

•••••••••• •. .

:;: ; ;:, . :'

~

.. "'",.'"."

•• '. : .. :.;: ~ I~ .000 .000 .000 .. .• .....

" : :: :: .. : '\ " . .. ,.

.: ; :' ··

25.000 .:: 127E55F :"'Ik.'\; ..... ... ;.; :.;.:: : ::. ''r-- ,', ...

•••• ' I ::.

~ i .• .. : .•. :: .'::; . "·: ':" : : ~'\ ;"it 1 AERODYNAMIC

:';' ' ' ••

. ' :' ... :: ::. · .:: :.

T\" 1\ ~ I •. 5 1 . ..,.

..

16N2SW VALUES THETAN THETA" ELEvON SPOBRK ....

" :'....

...... .' iii ::':'i'

~r"~

, . ' ~ .

: :.: ••• :':: ::: :i.' ::;i 111' .

'(~ :1 "Il.. "i.

: : :.': , ...

.169 .000 :. .: ::.

1.190 2.000 2.000 :.;.

: : .. .......

~~ ~ 1'::"'1>' 1' I " I ' I PARAMETRIC 3 "' ....

•••• ;';. :.

~ : ·: : B6SC 12G20M LONGITUOINAL ,.. :..

......

"""'~ ; .

.::: ,. I . 04 "AC~ BOFLAP PHI-N PHI-" RN/L .'

163 i

FA

: :i:,'i" ..:

:::." '

I OA .

.:.

.: '.

.: 1"1 1 I 1 FIG.

.000 0 5.000 8ETA 10.000 -5.000 -10.000 030 040 03qRt--.i:" 025 020 015 01 005 01 013 020 025

.035~

~

...

< (AFF003) SYMBOL u

:1 :: xa za '0 "J : L , ~ ·.

;;; INCHES INCHES III. IH. IN.

SO.FT.

I:I

I!

.. '::, > " .," .".

I

FI •.

":': ' '::' ·

": 111·1

GE ',' : INFORIIATIC'" " . ,."

.7 -0000 . .0405

I:!H 18 PA

,.

"

!

",' ..

474.8100 936.6800 37~,OOOO ":; 2690.0000 .

'11 "II"!"! , ..

.' • '".,'''''''''.''' ... :

fl

r': .. .......

; : REFERENCE .....

xMRP vHRP ZMRP !!; :': SIIEF LREF 8RE" SCALE ITTTTI 11'1 :

rl

III

IG .

" ·

' ,'"

..

:: ";'::: ". ...

1I II

."

..

r / .. ,',.......

:1 1 rT

"

:: '" .........

'

!lm! r 1·1

1'1

: .

r: I

'1' "

'

.":: ll

!

"1

Y

.,

' t! . 1

" , l l I !:, II '::

!IFII

I · 11

t '

..

o ....

' .11 ' )'"; :.: ..

~

', ,.:, I I 1·1

11 11

: COEFFICIENTS

.

I

:

" .'

., <".

I \:

"

!

'11 :

1 II

.000 .000 ,000 ', ..

15.000 I ,

I

I

,.

I 11 ....

AERODYNAMIC >, ..

1111111

fil

,IY . I ' I

VALUES SP09R" lHETAN THETAM ELEvON ",,

11 ,<

II

fl 4 DINAL

"

U I.

' "

.169 • 2.000 2,000 1,190

11 I

PARAMETRIC :':' 11111

- ..

'

..

,'; /f;.V

I . .

BG8CI2G20MIGN28WI27ESSFIOV8RSX9 LONGIT ....

~'(I' I , " ..

~.'" :7 MACH BOFLAP PHI-N PHI-M RN/L 2;; .';";: <'.'

OAIG3

"1

t ~

111111

1 11111

·1 FIG.

.oao 5,000 I;) 1' . . 10 10

4: v-'

O~

::;'

BETA -5, 10,000 -10.000

~

c

z u CAr-F003) SYMBOt.

,

:: J

.. :: .J

YO 10 :' .::: :::: .. :: ,:::

:,:: :::: ":'

..

;. 20

.

•. :

'" '.;,;; :,:: .. : ::, . . ." <

INCMES IN.'O IN.

INCMES IN. r.: 1 1 SO."T.

iaN . 1'1 •..

:' ...... ::: . ,'

:: ::. :: ..

,:, ::,' : 1 ::,.

1' F 1

III

+: r

j , > " 1:;: ' :.:: ::: :;1

,,: ". ::: ... ..... ....••

I

. :: 0000 .::::: , INFORt1Ai ,,,: :;' . .0405 I:':

:":: 1 iC 1'1'

PAGE : :':

.:: 1.:: ": "1

,:;' .••.•...

•• 474.0100 936.6900 ]75.0000 1076.7000

2690.0000 ElM

"

•• ::.: 1:

J

:' ': .... :,,:

111'

R'£FER'£NCE .• ' : ,. . , :"':

",' . ." . ,: ·

SREF LREF BREF .HRP 'HRP 1HRP SCALE

III

' "" :':' "" I ;;.;:;:': ,.: .

.. :: .: ...

•. :::

1 ' 11 11.1

1/1 I: : :;' ::

II

J: .•••

:1 15

. <;' """ 11 ::

t

;,;:

IT

1.1 :, '1: TlllT ................

:: ' .•.•••• ::: 1' I : ..

::

: .. •

...

!I!!}'

: " .

';, :. ..

I

<

1'1 12

'-f--'.+'-'-I--l---1 : .

:I

,,": ' .....

I

1 Irlrl

:.'

:.:: 1

. 1

:: T

:' : ,:: >'

:; : '

,, '. liT

I

..... '

.. ,: ,: .

,;:: oc 1": I , .....

::: ,.

' ~ I'>

IT IIIII

II (, : ....

..

:::: VI 1 j ~ >.':

.::,'::;, '

~ 1 :: 1 " 1 I +.-I--l-+-"-l-++-- COEFFICIENTS .. .'

"" :,,' :':' "" :::: :::: . ',;' IOV8R5X9 .

.. "' · I :: ::::

I 1111

JIII

~

... ' '.' <>

':: ,: ,,:

I 1

.000 .000 .000 :,;;'.' ..

:: ',' ..

.15.000 !'- :. '.

127E55F

:: . "1 ' • .•

.:'

1 Irll

AERODYNAMIC

'

"' ,: .: :',;;,; " , VALUES THE"" THE"" ELEVO" SPOSR" 1 11

I!

'1" :1/::

.. .. ··

::: .::.

.

1"

I

'''' ,'

.1

..

"

4-1--I-+-+-'-H-t--+- :

I'

''' .169 .000 12G20M 16N28W

'·

1.190 2.000 2.000

:1

1 -

PARAMETRIC :''' ,;' ::.

I

B68e H LONGITUDINAL

::,: .:.

I" 1 - ,

>

' 1 1' 1 '· : I '

1 '

.. :: "'CH BOFL'~ PHI-" PHI-" ANIL .....,;; ' 163 II' 1' 11 .

~ , ': ·· . ......

..

:: I 1' CIA • =1: ': •.

" :.

'.' :: '::

11111 I -

FIG.

.1 .000 u J 5.000 BETA -5.000 10.000 -10,000 026 002 022 020 01° 016 014 012 010 uue> oo~i 002 .024

~

AFF003 E U ( SfH80L - .

.

'j .. .. :: :: ::: ..

YO ; xa 10 . .

" , . . . . .. :: :;:; 1"

l!

j 'l

.: .

'. . . ·I " ': 20

.," : : :;": . -:: .. ::;.: .: .,: H ,:;. ,::: INCHES INCtES IN. IN. IN SO.FT.

: .... LJ.2

U

... " ,.

..... ":: ., i : -:- ::: - .•

F :· Il

,

. f ilm . j.;..j

, .....

.

.. . . . .. .

"1

,,', .::' ..... " . . :',· :..::: ' , ...

!

f::: 11 ,1· .........

::

:::.: '1

I,*,ORI1ATlaN ::;. ,:: ....... . .;:~ ::::':: ,',

.0000 .0405 :": 1 ··

, ., ...

PAGE .

::: ::,::.

~ :;,' .... . ,':: 375.0000 :... .,.

474.9100 936.6900 II·I , 1076.7000

2690.0000 ' l' .'

'" ' ..............

.• ,. ."': . ... ":: ." ,:;:

I: 1' 11 1'.1:-/

. !I

'

: ..

.': :; . H, .• ·: '.. ":: :;::

·····

1 , ..,

REFERENCE 1

1.

.. .

.

" 1 :: YI"IRP :; :.,. :;:: .::, .::,.. ...•. ... - ... ':: H', SREF LREF BREF Xt1/lP 1t1RP SCALE , S,

l 1