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NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONt
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https://ntrs.nasa.gov/search.jsp?R=19740013409 2020-02-14T20:57:22+00:00Z
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
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
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
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
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
|
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
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
|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
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
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
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
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
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
$RB (2) 4_2.12 ft.2 0.9265 in.2
Pitching moments were corrected for the effects of orbiter and fairing
base drag in the following manner:
CLM - CLMU - CABF _Z2 - CABO Zl , pitching moment coefficientIref iref corrected for orbiter and
fairing base drag
where
.yCLMU - qSreflref ' balance measured pitching moment coefficient
Z1 = 1.332 in., vertical moment arm for orbiter base drag
Z2 = 0.680 in., vertical moment arnlfor fairing b_se drag
10 1
1974013409-014
|
Axlal force coeftlclents were determined as _ollows:
FACA = - ..... , axial force coeffic_,,nt
' qSre f
CAF = CA - CABO - CABS - CABE - CABF, forebodv axial forcecoefficient
CABO = -CPBO Ab° , orbiter b,_¢e axis1 force ,-oefficientSref
CABS = -CAPS Abs , SRB base axial force coefficientSref
AbCABE = -CPBE e tank base axial force coefficient
Sref
CABF = -CPBF _Abf , fairing base axial force coefficientSref
Where:
Pbo - PCPBO - , orbiter base pressure coefficient
q
Pbs - PCPBS - , SRB base pressure coefficient
q
Pbe - PCPBE = , tank ba_e pressure coefficient
q
Pbf - P_CPBF _ , fairing base pressure coefficient
q
Ii
1974013409-015
TABLE I. _"
T E S r" TWT-589 (!A-62F) ] 1DATE i±-1_-7_
TEST CONDITIONS
MACH REYNOLDS DYNAMIC STAGNATION STAGNATION
NUMS£1_ NUMBER PRESSURE TEMPERATURE PRESSURE(per Unit length ) (poumds/$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
ti
,...1
1974013409-017
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
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
_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
!
• 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
1974013409-022
%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
1974013409-024
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
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
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
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
1974013409-029
: 26
| " I
1974013409-030
1974013409-031
¥
1974013409-032
!
DATA FIGURES
(
i '29
i
I
1974013409-033
~-
1974013409-034
1974013409-035
I I
1974013409-036
1974013409-037
I
1974013409-038
lrt,1 I l i
1974013409-039
11
....! :,. . i :.... :.::::.:- --| .....
-i >" .... I/'1 "--'
..... t I" _
..... t .... j, ,., , ......... a2
........................ :............. :..:!::.:,: ....... ___-' "" " _t::::':i:: 21:2 c__
. . '..................: :, ':'B_:
1_ i::i ::::im
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1974013409-133
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1974013409-134
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1974013409-135
ii
1974013409-136
APPENDIX
TABULATED SOURCE DATA
Plotted Data Tabulations Available
From DHS on Request.
1974013409-137
- I
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1974013409-138
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1974013409-139
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1974013409-140
i i ............
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1974013409-141
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1974013409-142
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1974013409-143
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1974013409-144
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1974013409-145
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1974013409-146
1974013409-147
lit
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1974013409-148
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1974013409-149
1974013409-150
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1974013409-151
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1974013409-152
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1974013409-153
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1974013409-154