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NATIONAL AERONAUTICS AND SPACE ADMINISTRATION t ! & _,CCKa_LL S['AC_ ' h_,_i_, i:,2,:,G.'PA'..£b VEHI_.L AE[O_NA_.IC ChA: AC.E:.L.:I LC_ _, (Citiy-._lei Ut,cla_ Cor_.) 152 _ fIC $10.75 CbC_. ,'.'u _,J/Jl 3o;_5J : ? 2 .. SPACE SHUTTLE " _'":'_' "::'"" _i ' ...... AEROTHERNODYNAMIC '' ' .,:. ""U..._.. DATA REPORT .,. .!.._ : .,," :_.'J;.4<: | '?",.': :r ;b : .:_:.ii/,::!,7.:< JOHNSON SPACE CENTER ''' :"";_:'::':_:..' ;":": _aT_ _J_agement services ..,, "T" ,,_ :,,...,. _..,,.,.._ ,...: . 3 https://ntrs.nasa.gov/search.jsp?R=19740013409 2020-02-14T20:57:22+00:00Z
Transcript
Page 1: NATIONAL AERONAUTICS AND SPACE ADMINISTRATION · 2014-10-01 · ON A .004 SCALE MODEL ROCKWELL SPACE SHIfI_LE | INTEGRATED VEHICLE AERODYNAMIC CHARACTERISTICS AT MACH WJMBERS FROM

NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONt

!

&

_,CCKa_LL S['AC_ ' h_,_i_, i:,2,:,G.'PA'..£bVEHI_.L

AE[O_NA_.IC ChA: AC.E:.L.:I LC_ _, (Citiy-._lei Ut,cla_

Cor_.) 152 _ fIC $10.75 CbC_. ,'.'u _,J/Jl 3o;_5J :

?

2

•.. SPACE SHUTTLE

" _'":'_' "::'"" _i

' ...... AEROTHERNODYNAMIC ' '' .,:. ""U..._.. DATA REPORT.,. .!.._:

.,,":_.'J;.4<: |'?",.': :r

;b

: .:_:.ii/,::!,7.:< JOHNSON SPACE CENTER''' :"";_:'::':_:..';":": _aT_ _J_agement services ..,,"T" ,,_:,,...,. _..,,.,.._,...: .

3

https://ntrs.nasa.gov/search.jsp?R=19740013409 2020-02-14T20:57:22+00:00Z

Page 2: NATIONAL AERONAUTICS AND SPACE ADMINISTRATION · 2014-10-01 · ON A .004 SCALE MODEL ROCKWELL SPACE SHIfI_LE | INTEGRATED VEHICLE AERODYNAMIC CHARACTERISTICS AT MACH WJMBERS FROM

i Mareh, [97h[

DMS-DR-2103

NASa.CR-IBh,ogh

WII%D TUNNEL TE_T RESULTS OF FAIRINGS

ON A .004 SCALE MODEL ROCKWELL SPACE SHIfI_LE

| INTEGRATED VEHICLE AERODYNAMIC CHARACTERISTICS

AT MACH WJMBERS FROM 0.6 TO h .96

(IA62F)

By

Ed Allen and Tom Hamilton

(Rockwell In'ternational)

Prepared under NASA Contract Number NAS9-IS747

by

Data Management Services

Chrysler Corporation Space Division

New Orleans, La. 70189

for

Engineering Analysis Division

\

Johnson Space Center

National Aeronautics and Space AdministrationHouston, Texas

1974013409-002

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WIND TUNNEL TEST SPECIFICS

Test Number: MSFC 589

NASA Series No.: IA62F

Date: November 15-19, 1973 (19 Occ. Hrs.)

FACILITY COORDINATOR:

Jim Weaver

Marshall Space Flight Center

Mall Stop S&E-AERO-AAE

Huntsville, Ala. 35802

Phone: (205) 453-2513

PROJECT ENGINEERS:

E.G. Allen Tom Hamilton

Southern Region Office Rockwell International Space DivisionRockwell International 12214 Lakewood Blvd.

Holiday Office Center Dept. 390, Mail Code AC-07

Huntsville, Ala. 35802 Downey, California 90241

Phone: (205) 881-2200 Phone: (213) 922 4820

DATA MANAGEMENT SERVICES:

This document has been prepared b_: /

J. E. Vaughn i _ _ // /Liaison Operations ,,_ __Z_-_

G O McDonald /_//'/

Dita'Operations ._./_,"_, P__

This document has been reviewed and is approved for release.

_N. D. KempData Management Services .q. _. _

UChrysler Corporation Space Division assumes no responsibility for dat_

presented other than display characteristics.

1974013409-003

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QNIND TUNNEL TEST RESULTS OF |AIRING$

ON A .004 SCALE MODEL ROCKNF.LL SPACE

$1fOTTLE INTEGRATED VEItICLE AE_0D¥1fi_IIC

CHARACYERICTICS AT MACU I_BERS FR_ 0.6 TO 4.96

(IA62F)

By

Ed Allen and Tom li_mllton

(Rockwell International)

ABSTRACT

Experimental aerodynamic investi8ations were conducted on a .004

scale model (34-0TS) orbiter, external tank, and solid rocket booster

combined a8 an integrated vehicle in the NASA_qSFC 14 x 14 inch Trisonic

Nind Tunnel. The primary tes_ objective was to determine the effect of

a fJil length orbiter/external tank fairing on axial force. Secondary

objectives were to define the static stability characteristics of the

mated vehicle configuration with fairings over a Hach number range of

0.6 thru 4.96. Six component aerodynamic force and moment data were re-

corded over an angle of attack range from -10" to 10 ° at 0" sideslip

angle and from -10" to 10" sideslip range at 0 ° and 5" angle of attack.

Plotted and tabular results are presented herein.

\

(" PRh_CEDING PAGE BLANK NOT FILMED

iii

l ! I

1974013409-004

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1

TABLE OF CONTENTS

ABSTRACT i!i

[

INDEX OF MODEL FIGURES 2

INDEX OF DATA FIGURES }

NOMEN ',ATURE

CONFIGURATIONS INVESTIGATED 7

TEST FACILITY DESCRIPTION 9

DATA REDUCTION I0

TABLES

I. TEST CONDITIONS 12

II. DATA SET/RUN NUMBER COLLATION S_Y 13

III. MODEL DIMENSIONAL DATA 14

FIGIrRES

MODEL 25

DATA 29

APPENDIX - TABULATED SOURCE DATA

1974013409-005

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INDEX OF MODEL FIGURES

FIGURE TITLE FAf;E

l Axis Systems 25

2 General Arrangement of the Integrated Vehicle Model 26

3 Side View of the .004 Scale Model 34-OTS Installed

In the NASA/MSFC 14 x 14 Inch Wind Tunnel 27

4 Base Pressure Measuring Tube Locations 28

2 (5

- ,]

L

t

] 9740] :3409-006

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|

INDEX OF DATA FIGURES

PLOTTED

TITLE COEFFICIENT PAGESSCHEDULE

Effect uf Fairlng8 on Integrated VehlcleLongitudinal Characteristics A 1-]5

Effect of Falrinss on Integrated VehicleLateral-Directional Characteristics (Alpha - O) B 36-51

Effect of Fairinss on Integrated VehicleLateral-Directional Characteristics (Alpha - 5) B 52-71

8age Axial Force Coefficients of InteKratedVehicle Components C 72-103

Plotted Coefficient Schedulas:

A) CN vs CLM; CN, C124, CAF, CA vs ALI_A

B) CY vs CYN; C¥, CYN, CBL vs BETA

C) CABO, CABE, CABS, (CABF where appllc_ble) vs ALPHA or BETA,as appropriate

(

3

1974013409-007

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NaMmCLATUREOenerol

SADSACSMK) L SE_)L DBI_J_OJl

8 speed of sound; a/sec, l_./_ec

CP pressure coefficient; (P1 " Pe)/q

M NACH Nsch number; V/s

p pressure; H/m2, psf

q Q(_) _m.-,c _,,_; l/2,_, a/,2, p,f

I_/L _/T. unit R_olds number; per m, per

v velocity; m/Ne, _t/sec

ALPHA angle of 8tt_ck, 4e/_es

BETA 8nsle o1' sldesl£p, delrees

PSI angle Of yn, de6rees

PHI snsle of roll, de_es

p msss density; k_/m 3, sl_x_S/i_t 3

Reference & C.O. Detlnltloas

Ab bsse ores; _, tt 2

b JR_ vlng spsn or reference spsn; n_ _t

c.g. center of _revity

_U_ LR_ reference len_;b cr vln8 J.snsero_nsa£c e_ofd; a, rt

S _ ,_g ares or reference sres; s 2, ft 2

lip ac_nt reforon_ point

,.oment reference point c_ X sxis

_P Bclent reference po£ut on Y sxls

W uc_ent reference point on Z 8xls

_B6CRIPT5b bsse1 loesls etstAc conditionst totsl ec_4LIktms® f_ee strns

a

1974013409-008

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|NCM]MCLA_UILE(Continued)

_-Axls S_stem

SADSAC

s_mo_____smeoL DmT_O_

C_ C_ nol-mal-force coefflclen%; nca'_nlqSfOa'oe

" CA CA axlal-force coefflcle_Z; axial fo_ceqS

Cy CY st4e-force coefficient; side forceqs

CAB base-force coefficient; base forceCAb q_

-Ab( _ - p®)/qS

CAr CAF forebody axial force eoefTlctent, CA - CAb

Cm CIM pitching-moment coefficient;

Cn CTR yewlng-mcment coefflr%ent; _a,wtnl momentqSb

C_ C_L rollin6-woment cc_.fficlent; rol_/nl momen_• q_b

Stab111t_-Axls _s_

CL CL llft coefficient; Lift

CD CD drag coefficient _

CDb CDB base-drag coefficient; base.qsdX_

C]_ CDF forebody drsg coefl_clent; CD - CI)o

Cy CY side-force coefficient; side forceq8

pitch,_m_ntClbl ptt_hinS-momn% cotft_cteut _ qS_l_ l

Cn CLN ya_inS-moment ¢oefftcteut! _ . i

C_ CSL rollins-moment coefflc£ent!

r.,/D Z./D _._e_-to-e.-.,_,,_so_ cr,/cD 1

$#

1974013409-009

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NOMENCLATURE.

" (ADDITIONAL TO STANDARD LIST)

DMS

SYMBOL SYMBOL DEFINITION

CAB0 CABO axial force coefficient due to pressureforce on orbiter base

CABE CABE axial force coefficient due to pressureforce on external tank base

CABS CABS axial force coefficient due to pressureforce on _olid rocket booster base

CABF CABF axial force coefficient due to pressureforce on fairing base

io ORBINC angle between the orbiter water plane'_,00line and the external tank center

llne, degrees

Zo DELTAZ minimum vertical separation distance

between the orbiter and ex%ernal tank,inches

Pb orbiter base measured pressure

Pt, SRB base measured pressure

!i,_ external tank base measured pressure

?b_ fairing base measured pressuv_

6

1974013409-010

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ti

CONFIGURATIONS INVESTIGATED

As a part of the continuing drag reduction program for the mated

_ehlcle a full length (orbiter) fairing between the orbiter and external

tank was tested on the O.004-scale mated vehicle model (34-OTS). The

orbiter used in this test was the vehicle 4 configuration (140 A/B). The

tank was m_'_,,tedon the sting/balance combination with both the _rbiter

and SRB's rigidly attached to the tank. The model geometry (0.004-c

is shown in figure 2. Figure 3 is a side view of the model installe

the tunnel. The configuration designation is given below:

Orbiter (034 modified to 140 A/B)

B26 Body

C9 Canopy

R5 Rudder

V8 Vertical tail

WII6 Wing

F7 Body Flap

E26 Elevon

M7 OMS pods

TI4 External tank with LOX and LH2 Vent lines andLOX feed llne (PT i, 2, 3)

PT4 LOX vent fairing on tank nose vertical centerline

S12 Solid Rocket Booster with attach ring (PS2) and

separation rocket fairing (PS3)

FR4 Full length orblter/ET fairing

T9 External Tank J

7

T

I II !

1974013409-011

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The speed brake, rudder, and body flap deflections were z_'r¢, t_r the

entire test. The orbiter/ET incidence angle was also zero.

li_cexternal tank was mounted on the TWT 232 balance which w4s _up-

ported by the number 3 balance adapter and sting. The orbiter was mounted

to the tank at three points simulating the forward attach point and the

two main fuel lines for the rear attach points. The SRB's wt,r,,al_,

rigidly attached to the tank.

Base pressures were monitored at the six locaClons shown in Figure,

h. A total of four base presoures were recorded. The two tuves monitor-

ing the orbiter ba, _ pressure were "teed" together, as were the two tubes

at the base of the external ta'ik. The four base pressures recorded then

were the orbiter, tank, solid rocket motor and fairing.

Model dimensional data sheets defining the various configuration

designators are presented in Table III.

\

\

8

I !

1974013409-012

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gi1 TEST FACILITY D_CRI}_UION

The Marshall S?_ce Flight Center lh" x lh" Trlson[c Wind Tunnel [_ nn [nter-

_littent blowdown tunnel which operates by high pressure ',It flowing from

st_r_ge to either vacuum or atmospheric conditions. A M:_c_ _,umber range

from ._ to 5.85 is covered by ubillzing two interchangeable test s_ctlonc.

The transonic section permits touting _t Moo:, 0.2C through .:3©,and tnc

supersonic section permits testing st Mach _.Th through q.Pq. Msch numbers

between .? and .9 _re obtained by using s corltrollable diffus,_r, m_.......

from .95 to 1.3 is achieved through the use of ph:num suction and perforated

walls. Math numbers of l.h4, 1.93 and _.50 _- produced by interchangeable

sets of fixed contour nozzle blocks. Above M_h 2._0 s set of fixed contour

nozzle blocks are tilted and translated 8utom_tically to produce any desired

Mach number in .25 increments.

Air is supplied to a 6000 cubic foot storage tank st _pproximstely -hoOF _eu

point and 500 psi. The compressor is a three-_tage reciDroc_,ting unit dri_

by a 1500 hp motor.

The tunnel flow is established and controlled with "__;ervo_,ctu_ted gate

valve. The controlle; air flows through the valve diffuser into the stilling

chamber and heqt exchanger where the sir temperature c_r,be controllem from

_mbient to approxlmstely 180°F. The _ir then passes through the _est section

which contains the nozzle blocks and test region.

Downstream of the test section is a hydraullcslly controlled pitch sector

that provides a total angle of attack range of 20o (+_i0°). Sting offsets are

available for obtaining various maximum angles of attack up to 90°.

9

i

9740 3409-0 3

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DATA R£DUCTION

All model forces and moments were resolved in the body axis system

and presented in the form of nondimensional coefficients.

Data were corrected for weight tares and sting deflections.

Model reference dimensions used in the data reduction for this test

are presented below:

PARAMETER FULL SCALE MDDEL 5CAI.E

Reference Area (Sre f) = wing planform area = 2960 ft, 2 6._98 in. 2

Reference Length (lref=bref) =orbiter body length ffi 1290.3 in. 5.160 in.

Moment Reference Center, from

tank nose on tank _ 670 in. 2.680 in.

Base A,eas

Orbiter 417.4 ft.2 0.9617 in.2

Tank 572.55 ft. 2 1.319 in. 2 ,

Fairing 107.7 £_.2 0.2482 in.2

$RB (2) 4_2.12 ft.2 0.9265 in.2

Pitching moments were corrected for the effects of orbiter and fairing

base drag in the following manner:

CLM - CLMU - CABF _Z2 - CABO Zl , pitching moment coefficientIref iref corrected for orbiter and

fairing base drag

where

.yCLMU - qSreflref ' balance measured pitching moment coefficient

Z1 = 1.332 in., vertical moment arm for orbiter base drag

Z2 = 0.680 in., vertical moment arnlfor fairing b_se drag

10 1

1974013409-014

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|

Axlal force coeftlclents were determined as _ollows:

FACA = - ..... , axial force coeffic_,,nt

' qSre f

CAF = CA - CABO - CABS - CABE - CABF, forebodv axial forcecoefficient

CABO = -CPBO Ab° , orbiter b,_¢e axis1 force ,-oefficientSref

CABS = -CAPS Abs , SRB base axial force coefficientSref

AbCABE = -CPBE e tank base axial force coefficient

Sref

CABF = -CPBF _Abf , fairing base axial force coefficientSref

Where:

Pbo - PCPBO - , orbiter base pressure coefficient

q

Pbs - PCPBS - , SRB base pressure coefficient

q

Pbe - PCPBE = , tank ba_e pressure coefficient

q

Pbf - P_CPBF _ , fairing base pressure coefficient

q

Ii

1974013409-015

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TABLE I. _"

T E S r" TWT-589 (!A-62F) ] 1DATE i±-1_-7_

TEST CONDITIONS

MACH REYNOLDS DYNAMIC STAGNATION STAGNATION

NUMS£1_ NUMBER PRESSURE TEMPERATURE PRESSURE(per Unit length ) (poumds/$q.lnch) ((legrees Fo_e.heit', ( _ounOs/S(l inch)

-, ,=

0.6 _.0 x 106/ft .-. - , iOO 22 ,

O.9 6.2 7.37 lO0 22

i< 6._ c -•_ . '_".:'" i00 22

1.2 6.7 9.2_ iOO 22m , n, ,

1 46 6.5 _'_ i00 22

2.99 _.O 5.19 140 30j,,,,

_.96 _.8 3.07 140 90

,, , , =,,

BALANCEUTILIZED: MSFC 232

COEFFICIENTCAPACITY: ACCURACY: TOLERANCE:

300 ibs. _1.50 ibs. ±O.O2hNF ,,

SF !45 ibs.. .+O.72 ibs. _O.O12

AF ,50 ibs.,, ±0.25 ibs. +O.OOh

PM L_OO in. -ibs. -+2.OO in. -Ibs. ±0,006

RM iO0 in. -IDF. ±o.50 in. -lbs. ±O.OO2-

YM 192 in. -lb, s. -4"0.96 in. -ibs. +0.00_

COMMENTS:Accuracy based on +0,5% of balance capacity.

12

1974013409-016

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ti

,...1

1974013409-017

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TABLE III. MODEL DIHENSIONAL DATA

_ ...... _. : BC._Y-

GEt_E:ALDESCP,IPTIO:(:Orbiter Fusela£e ConfiRuration 140 A/B

NOTE: L_ c identical _to ....g_,_ except underside of fuselage refairLd to

accept "iiO"

godel Scale = .OOhi

VL70-000193

DgAWI"" '"".'_-:_",,_,.......... VL70-000] 40A

DI.V.ERSIONS: FULL-SCI.LE _IODELSCALE

Length (£ody R,'dSta Xo = 238) - in. r 1290.3 5.16120

_ax. Width [at Xo = 1520) - in. 262.0 l.OhSO0

i Max. Depth (at Xo = 1464) - in. 250.0 1.000

FinenessRatio 4.92481 4,924si

Area ft2

Ma_. Cross-Sectionai 340.8g462 O.005;_5

Planform

Wetted

Base ............

: i\

1974013409-018

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e

ITABLE III. - CONT.

|' MODEL COMPONENT: ".-'[c"T - ,",_

fI.

GENERAL D._SCRIPT!ON: Ccnfi_ur_-tion3)

l'odelEce.le= .O.Ok

VL70-OOOIAC.',DRAWING NUMBER . V],70_OC©]I,_.'.

I)Ir,AENSION: FULL SCAL[ MODEL SCALE

Length (Xo=_3&.6&3 to 670) 235.357 0.9_1_3

Max Width (C,i:o=5!3.127) 152./12 O.___T-6_

Max Depth (_ Zo=.k'SS.C) 25.000 O.lO000

FinenessRatio

_teo

Max Ctos_.-Sectionol

Planform

Wetted

Bose

\

' 15

,b

t I " SD73-SH-O061

1974013409-019

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_T TABLE III _ CONT.

/MODEL COMPONEN'T: :-_--. _"__.. _ V.

jr

GENERAL DESCRIPTION: qcr.F-_':_.°.'cn 2

l'_.Z: "_'_'" "" "s ".-..'-"'" ..... ,'7i".-- _:'"',_"":_" of -'13 '75° --'_

-!/,.,"::. "_ fr:- :.":.Z .,arit-_,r. '.'in -_. lin_ !cr_.t".i LL ""o ::-5,2¢._,

'3' --= LC_..)

_:o'i'_-2 7":'.1-- = . 004DEAWI NG ' "'" , ........NU,,"_o-'-P, VI.70- CCD!:,C., ', '0 -r',,• .--5

DIh',ENSIC 1: FULL SCALE MODEL SCAL,r

ac

Len31hflc.:--i,:22 to X.o-_-'_ C_--''_) - I::. 93.009 0. 377.

Max Width - "r::. 262.C2.3 1. 048 "

23.,,.oMax D:plh (:':c :" --"_"_ c.-,_J _ I::. "" O. 092 °

Fineness Ratio {

Area - •, i

Max Cross-Sectional __ ]

Plonform ' "-.l.SD.._!O__ . O. O0Z41 _

Welted

Bose 41.84722 " O. 00067

!\\

16 (tQ

• SD73-SH-0061

|

1974013409-020

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!

• TABLE III - CONT. #o

lMODEL COMPON[I'JT: '_'_,_ :_"_..,- :'".. ;.

Jl i i q

I.

GENERAL DESCRIPTION. 2or.fiteration3A

i i | , , J

M>del c_ I:. "_ ,.... _ • JC¢-• 11 L

VLTO-CYgOI'¢,iDRAWl NG NUI¢.'3ER VL?O-C_,_345

DIMENSION: FULL SCALE MODEL SCA'E

, Lerx3th(0:-_h_d Sta Xo=1233.0) - IN. 327.000 1.30800

" MoK Width ('?Zo=l&50.O) - II_. 9h.5 O.37_0e) .f .

Mo_ Depth (_ Zo=!493.0) - I:I. 109.009 U._z_O0L m

• d.

Fineness Rot;o

Area

Max Cfoss-Sectim,al

PlcJnform_ I L__ M

Wetted

Bosei

t

/

• 17

P

"" i .,' SD73-SH-O061

| ' ,• I

1974013409-021

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1974013409-022

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%ABLE III- CONT. , •

i; I • "

MODELCO,.,PO,,-,_T" .-"L_.:c':- F..2_

(;EI,:EPALD SCRIPTI.P,.: Confi_'-r_ticn 4

I:07.",': VLT,0-O?_400 (-'.t; for (1) of (2) sides. Identical to E2S except

airfoil tl,i c],ncss

Eodel Sc_!e = .ooL

VL?O-O9$_<,O...._ VLTO-_S!ACDRAW]I_GhU,.,_.R:

FULL-SCALE I;ODELS.;,L[, DII4EI_SIO_S:

!

Area fl;. 223. 5814 o.00358, Span (equivalent) in. 96_,31_ =_1/_7336

]nbtd equivalent chord :In. 119.623 0'Z'78_9

Outb'd equivalentchord In. 55.1922 0.22077

Ratio r,;ovablesurface chord/total surfacechord

At ]nb'd equiv, chord 0.2096 0.2096

At Outb'd equiv, chord O.I,(X'}_ O._OOL

Sweep Back Angles,degrees

: '..,LeadingEdge 0,00 ..0.00

........ ' "- _ ' -:to.o.s6 -:to.o56• . -_.'TailingEdge - -

0.00 0.00Hingeline ..........

Area Mor,,en.t(_oi_alto hinge line) ..8_:I.150.2 ...0,o0o.05

19

SD'/3-SH-006]: ' . |

1974013409-023

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1974013409-024

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TABLE III - CONT.e

g.. MODEL COV,PO!'ENT: RUDDER - R5

BEtlERALDESCRIPTION: 2;,,3 and 3.kConligu_tion per Rocb,mll Lir_os

' VL70-05C395

• Model fic_!e = .OOh

DRAWl% I;U:4BER: VL?O-_CY2r_095

DIMEI_SIO_IS: FULL-SCALE MODEL SCALE

Area - r?2 !06.3B o.oozTo

Span {equivalent) - IN. 201.0 0.80400

Inb'd equivalentchord 91.SRSj_ 0.366]_

Outb'd equivalentchord _ 0.20333

C " Ratio r,oveb]esurfacechord/total surfccechord

At Inb'd equiv, chord 0._00 9.1,00

At Outb'd equiv• chord ,. 0.400 . 0._00,,

Sweep Back Angles,degrees

• Leading Edge . 3_.8_

•TailingEdge ._ 26.2_ 26.25

Hingeline _ 3_.83,. 3_.8)

Area _oment (Normalto hinge llne)-F?3 526_3 0.00003_m , , , ,

Product'o_ Area and Ilean Chord

21

SD73-SH-0061

!

1974013409-025

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TABLE III - CONT.

MODEL COMPO,'_E_IT: ExternalTank T9Ill i I •

GENERALDESCRIPTIOtI:2A ConfigurationPer firLines VL78-000018and '_L72-00_0_'_;

Body of Revolution

I

Scale _odel = .OO4

DRAWIII5,IU_ER. VL78-000018

_B£OR_TICA/, ACTUAL MF..ASU-<-:)i

DIMENSIOhS" 1_jI.I,-sc_.tJ_ MODKT. SCM_E IdDmrm SCALE

Length 1826.O0 7.304

Max. Width 324.00 1.296i

Max. Depth .....

F_n:_.nessRatio 6.13889 6.13889

Area

Max. Cross-Sectional 572.555 0.00916

Planform

Wetted

Base 572.555 O.00916

REF

FS (Orbiter)0.00 = TANK Station635.0 INFS

WP (ET)= 400 - 344.413= 55.587 INFS

BP (Orbiter)0.00 = 0.00 ET

22

• SD73-SH-0061,'

1974013409-026

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iI

' TABLE II1 - CONT.

|MODEL CO_PO';ENT' EXTF.P"AT. TAN v - m],_

GENERALDESCRIPTIOrI"

NOTE: T14 identical to Tn but with e:'ternal fuel llnes added.

Model Scale = 0.004

DRAWING;_U_:BER• VL78-000018

DIMENSIO:;S" FULL-SCALE r:ODELCC,'_

Length- IN. 1858 7.432: J,,

Max. Width (Dia) - IN. 324.0 1.296

Max. Depth

Fineness Rati0-L/D _ 5.73457

Area - F,T2

Max. Cross-Sectional 572.56 0.009161

Planform

Wettedi ,,

Base

23

' SD73-SH-0061 i

1974013409-027

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TABLE III - CO:,i',

GENZP_L 5E_Cq:PT]_'-_., Ccnficurat!Dn s:,'",_ta__ for _.'") of ,,_'"1

sides, zer =_'_-_l! LI.-_s VL77-,_,_,:

Model Scale = 3.004

'IL72-0000 ::,:,{)RAW,,,J VL77-0000 :_A

OIME;_S'C% • FULL-SCALE MODEL _C;.LE

Length (Includes ::ozzle) - IN. 1741.0 6.9640

Max. Width (Tank Dia) - IN. 142.3 0. 5692

Max. Depth (Aft Shroud) - IN. 192.0 0.7680

Fineness Ratio 9.06771 9.06771

Area - FT 2

Max. Cross-Sectional 201. 06193 O. 00322

Planform

Wetted

Base

kq_ of BSILH Centerline (ZT)- IN. 400 1.6000

FS of BSRM Nose (XT) - IN. 20C 0.8000

?

1974013409-028

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1974013409-029

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: 26

| " I

1974013409-030

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1974013409-031

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¥

1974013409-032

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!

DATA FIGURES

(

i '29

i

I

1974013409-033

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~-

1974013409-034

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1974013409-035

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I I

1974013409-036

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1974013409-037

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I

1974013409-038

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lrt,1 I l i

1974013409-039

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11

....! :,. . i :.... :.::::.:- --| .....

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..... t I" _

..... t .... j, ,., , ......... a2

........................ :............. :..:!::.:,: ....... ___-' "" " _t::::':i:: 21:2 c__

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

1_ i::i ::::im

... i I_[NI i •

_"" ," i': _.__,:- I:..... ! I.I.......... ' _ ' _ ""-_, I............ , ,,__- ...I .... , ..................................... I.... co

""- !I z'_-" ......... '................. I............ I.... I........ I....1.... I....... " -"_ i,- _,,,, °l oo,, o,, ...... °,., .... I ° .... ° ......_;_-- ......... :;:::: :::: ::::'::::1:::: :::: ::::1::::1:::: ::::l::::l::::l:::: :::" _ _z

i ........................... _............. I .I z

u_, ............................ I ,i ........ :i ......... u_

..................i...... '"'"'! ........I....!....!........" '-:............. °o, _ _

_ :::: :'..i .......................... i ............ _ ,., <

_li_li I I I I I I I I I

NO '1N_13I.-I.:1303 33_10.-I7¥H_ON

1974013409-040

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1974013409-041

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1974013409-042

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7

dlHnmm i iI

1974013409-043

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t

' I

1974013409-044

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II I I

1974013409-045

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tl

i ,,° ....... , ....... ° . °.] .... _

....... ._. _J

,(.... (./1.... r,..J

I....... . E" . ,-.,°'s

-_{l{! ...., i!i _. _:=-,..-_=Ill ............ I ............. ' ........ _ . ...n

ii

I. I. )ui° ° , I°

• _ UJ

_, I" 0

",_, .......... ,.

;_ ...... X =-"Z

-" I' " " m

( r4

_uUU ......................................... X 1.1..

' _ U

I_ _ I/1 ql' Iv) _1 ,- 0 -" _ _ qlr U1 _r_ I_ _ 011 I.hl u..--a;_ " " " " " ' " " " " " " " " " " " ,-,I I I I I I I I I

( N3 ' IN3| 3 [.-I-1_'40:)3:)lJO.-I"IVldEION

|mm l

1974013409-046

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1974013409-047

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0v-*

° ° °° ,4_

f -¢Y

.j .. _ .... _.... LtJ

_- - .t o. ° .°. ° ,°o° *o°, ,.,o ,.* * b°,,° e° .. _

......... _,=,,

• i n

_ii - :i _-°|

• e • • e e e i e _ _ e • * • e • e e • • • •

k_ee_ el o, e •

' _CC] '_,. "r

..... _.......... ' I.................... C._ _

( M3:) ' LN] 13 l.'J.'J30:) .I.N_dOM_N IH3t Id

1974013409-048

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1974013409-049

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: I

IIz,_ .....+................. +............. +...........

___--ZZZZZ ......................... P',.--o

,0..

!__+_+_l_l_.... "....._..... o

..................................................7 ii +0<t,. L.. t++ _._

t

.(

'_ _'_ iiiiiiiiiiiiiiiiiiiiiiliiiiiii!i+iiii/ .... _+-'+ i++ +.-_.! " - , • , +m° +.+

<I+I_ .................................... "--'_+.............. ./ <.+i

i ii,iiiii::i,....7 ......' '_ _ "-!-.... III

- ........ i+:i ! !!iii..................................... _z

++ f i*',. • • • • .. ,. • • .i • • •

++-ii............. ',"J " " dl_

:: ?_/: ........... . °°+++_......I" • ,+ , ,* e, ,, +* + ++ +, + +e ,. ,, • , _ i, ,, • • +, • ,* + II_

I.i.

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<++++ • • • . • . . • . . . . . • . ,.,+ ®+ e o o o o o

( M"I::)'IN31_I..,t.:I3D3IN3klO_ 9NIH:OIId

1974013409-050

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1974013409-051

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' e

I

N_w"_ • I Z

99

J....... _ _r'

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14"1::)* J,N3 | :2! :1:130:2 J,N314QI4ON[ H_)I |cl '

1974013409-052

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II

1974013409-053

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fl(",,I

'_'"'_,ii!!iiiii!iiiiii!i1!!!!'ii!i!!!ii!!i iiiiiiiiiit!iii'i I-oW ........ t,,._,)

i O0 ,---,

iiill........i .................._§ ................................ _,. -.......... _.<=

"'_ i!!!!i _ I o.• ° °° • . °° ° . • ° .° , ....

q ° ° ° °° ' • • ° ,, b, ,. ° ° °. , ° • •

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Z __ ° *. • .Q • • . ,° . . . •

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|

1974013409-054

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1974013409-055

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1974013409-056

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I m | ,

1974013409-057

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|-- _zzzzz .......... _,_

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l 4 ................ L,k _

_ "1__ ................ <• • • • • • • • • • • • _ • • " • " • ° ° " * ' • ° " " ° * ° " " " ° " Z

_, ":i::: ::: i:: :i:: ....... F:_J20

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1974013409-058

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1974013409-059

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1974013409-060

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M

1974013409-061

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_J

mlmmm

1974013409-062

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1974013409-063

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1974013409-064

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t

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1974013409-065

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/

1974013409-066

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1974013409-067

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1974013409-068

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I II _il!i Ill I I

1974013409-069

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1974013409-070

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ii

1974013409-136

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APPENDIX

TABULATED SOURCE DATA

Plotted Data Tabulations Available

From DHS on Request.

1974013409-137

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1974013409-143

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1974013409-144

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1974013409-148

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1974013409-150

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