BASEPHESSU ={EAI' H ATTP&2']SFER ±S.SCF TEE '.' …...Tabulated heat transfer and pressure d_a__are...

$Page 1: BASEPHESSU ={EAI' H ATTP&2']SFER ±S.SCF TEE '.' …...Tabulated heat transfer and pressure d_a__are not _oresented -_r,_ this report; they may be obtained as sho_m in Appendix A.$
3 1176 00135 3821

N/ ANationalAeronauticsand NASA-CR- 151776Space Administration 19790078847

LyndonB. JohnsonSpace CenterHouston,Texas77058

r' '-_

i DMS-DR-2453NASA CR-151,776

BASE PHESSU_={EAI'_H__ATTP&2']SFER,'±S.SCF TEE __'.'_'¢-,j--D-

SCALE SPACE SHUTTLEPLI£.4ESIYULAT!0i_MODEL (19-OTS)

I_ _.E IiASA/CA!SPA_fLUDWIEG_J-SE:.'_i'_ TU}_L ( .. I,,,

imilr, _ .... llr

JUL J 19/9

,II._NGLEYRESEARCHCEN'[E]]LIBRARY,NASA

H_AM__Io_,.VI2.GI_I.I_

DC_tC_ m_"_"_AGEMENT SERVICES

s.Aceo,v,slO_@ CHRYSLERCORPORATION

https://ntrs.nasa.gov/search.jsp?R=19790078847 2020-02-26T03:14:17+00:00Z


April, 1979

DMS-DR-2453

NASA CR-151,776

BASE PRESSU_E A_[DHEAT TF_5_SFER TESTS OF %I._EO._-_D -

SCALE SPACE SHUffLEPL_,[ESI}_J_4TIONMODEL (19-OTS)

IN THE ".,,_SA/CALSPANLI/DWIEGTUBE _.,"INDTUNq,FEL(IEi75)

by

J. W. FousZ C.E. Wittiiff

STS Aerosciences and Aerodynmmic Research Department

Rockwell International Ca!span Corporation

Space Systems Group

Prepared under NASA Contract Nmmber NAS9-!3247

by

Data Management Services

Chrysler Corporation Michoud Defense-Space DivisionNew Orleans, La, 70189

for

Di¢_s_o._ngineering Analysis "-_ _ _

Johnson Space Center

Nationa! Aeronautics and Space Admlnls_a_.on

Houston, Texas

_:;-!_[DDTLr_,_L"-_<__.__,SPECIFICS:

Tesz Nt_-.foer: Calspan LT I95-I00}_SA Series N_er: 1t-[75Model Nu__f_er: _y'^-OTo

Test Dates: September 23, 1977 tc December !2, 1977

Occupancy Hours : 320

FACILITY C00PdDI_L'\TOR:

C, E. T'T'_'_'I'I'P'_

Aerod_ma_ic Research Department

Ca!span Corporation. P.O. Box 235

Buffalo, New York 14221

Phone: (716) 632-7500, Ext. 720

PROJECT_,IGII,_EPS:

J. W. Foust C.E. Vittiiff

M. Quan Aerodynamic Research De!partmentMai! Code AD3_3 P.C. Box 235

_,oci<:,_-iInte.__ationa! 3uffa!o, New York _k_21

Space Systems Group

!221L L_<ewood Boulevard Phone: (716) _o_-7500, _:t.720Do_ey, CA 90241

Phone: (213) 922-1451

DATA F_AG_<ENT SERVICES:

Preparedby: Liaison--D.W. HerseyOperations--G.R. Lutz

Reviewedby: G. G. McDonald

7

Approved:/ . _ Concurrence-//€'-_-_!,_ -, ....)

. Glynn_anager N.D. Kemp, ManagerOperaZi-_ns Data "_ - -__mna_eme_. _ Services

_n_jsler Corporation i,:ichoudDefense-Space Division asst_es no __esp_s,'_,__ -bility for the data presented other tha_n display characteristics.

ii

SCALE SPACE SI_U%_!__I_EPLU2,_SI_._-iATiONMODEL (!9-0TS)

IN _9_E_,_._%/CA_,c_P:Ai,JLU-D_.._EGTUBE;._}_'_-%_L(Z_75)

by

J. W. Foust C.E. ,.$1ot!___.

Rockwell International and Ca!spa.n Corporation

Space Systems Group

ABSTPACT

.es_ Z_75 was conducted in the iTASA/Calspan Lucwleg '_-hbe,:ind

tmmnnel to determine :_o*_ transfer _..._cresol.....__distributions and gas

recove._s temperatures in the base regions of a rocket firin_ model of

the space shuttle integrated vehicle. The distributions are a direct

result of rocket pl_me gas recireu!ation and impingement at simulated

first-and second-stage flight trajectory conditions. Tne objective of

this test was to extend the existing experimental data envelope to

hi_her Mach numbers and altitudes.

First-end second-stage flight trajecto_ _ conditions were simulated

by simultaneous flow of the space shuztle model rocket engines and

Lud_rieg Tube Wind Turunel into a vacuum enviromnent. __-_.rst.-stageflight

consisted of space shuttle main engine (S_:U<) and SRB rocke_ motor

simulation. Second-stage flight consisted of SS}_ simulation only. ._ne

Lud';ieg Tube Wind Turin.!!simulated Mach ntt_oers of 3.5 and k.5 over an

altitude rar_ze of i00,000 to 170,000 feet _.._ithva_jing ttu__neltotal

temperature, model angle-of-attack, nozzle gimba! angle, and B_RB ch_-_foer

iii

ABSTRACT (Concluded).

pressure. For first-stage flight, the I...._ a____u_e r__ge was i00,000 to

140,000 feet at Mach 3.5 and i00,000 to 160,000 feet at Mach k.5. Fcrd

second-stage flight, the altitude range _¢as 130,000 to 170,000 feet at

Mach _.p.

All objectives of Test IH75 were fulfilled Four runs were oo__n_d

at Maeh 3.5 to collect repeat data to verify that IH75 test techniques

would produce satisfactory data. At _[ach 4.5, twenty-three first-stage

r_ns and fifteen second-stage runs were obtained.

Tabulated heat transfer and pressure d_a__ are not _oresented -_r,_

this report; they may be obtained as sho_m in Appendix A. Gas recove_ _

temperature data derived from the thirteen gas temperature probe runs

are presented in Appendix B.

The model configuration, instrumentation, test procedures, _.d data

reduction are described in this report.

Procedures sm.d data from the flow calibration of the Mach 3.5

nozz1__ used ""_,_l_the Lud_ieg Tube _ind Tuu_nel for Test !H75 =._=_presented

in Appendix D.

iv

TABLE OF CONTENTS

Page

ABSTRACT iii

INDEX OF MODEL FIGURES 3

INTRODUCTION 5

NOMENCLATURE 6

CONFIGURATIONS INVESTIGATED 9

INSTRUMENTATION 16

TEST FACILITY DESCRIPTION 22

TEST PROCEDURE 25

DATA REDUCTION 35

RESULTS AND DISCUSSION 45F

REFERENCES 48

TABLES

I. TEST CONDITIONS 50

II. DATA SET/RUN NUMBER COLLATION SU_ARY 51

III. MODEL DImeNSIONAL DATA 53

IV. SOLID PROPELLANT SURFACE AREA 65

V. INSTRUMENTATION NUMBERING SYSTEM 66

VI. INSTRUMENTATION CONFIGURATIONS 67

VII. THEP@IOCOUPLES 85

VIII. MAXI_fUMMODEL 19-OTS OPERATING CONDITIONSIN THE CALSPAN LUDWIEG TUBE WIND TUNNEL 86

IX. DATA ACQUISITION SU_RY 87

F

TABLE OF CONTEI_IS(Concluded)

Page

FIGURES

MODEL _ 88

APPENDIXA

SOURCEDATAEZFE_[CES

APPkn_DIXB

GAS RECOVERY TEMPERATURE DATA

APpkn_DIXC

FM DATA TAPE CORRECTION

APPENDIX D

FLOW CALIBRATION OF _[&CH3.5 FIBERGLASS NOZZLE INNASA/CALSP.a_NI7!DWY]D3TUBE%_INNEL

2

iiDE< 0F _IODELFiGU._Z$

Figure Title Page

i. Gimbal _ngle definition. 88

2. Orbitervehicle. 89

3- Integratedvehicle. 90

4. Instrumentation.

a. Orbiter Side 91

b. O_siter Too 92

c. Wing Lo_yerSurface 93

d. Wing Upper Surface 94

e. VerticalTail 95

f. Body Flap 96f--

Le_ 0MS Pod 97

h. Left _S/RCS - InsideSurfaces 98

i. Left CMS/RCS- Aft Surfaces 99

j. Right CMS/RCS- Inside Surfaces i00

k. Right 0MS/RCS- Aft Surfaces I01

1. OrbiterBase Heat gnie!d 102

m. S_ FiringNozzles 103

n. HatbandNozzle 104

o. _te._al Tank Side,call 105

p. ExternalTank Aft Dome 106

q. _l_xternal___nkHardware 107

r. Le_ SRB Sidewall 108

F

3

Ii_( OF MODEL FIGURES (Concluded)

Figure Title Pa_e

£. Instrttmentation. (Continued)

s. Left SRB Nozzle and Shroud 109

t. Left SRB Skirt Curtain ll0

5. Short-duration Ludwieg Tube Wind Tunnel. lll

<_. Wave diagrs_mfor Tube _,JindTtunnel. ll2

7. Ludwieg _abe Free Jet Test Phomfousfor _[&_4£.5nozzle, ll3

_. Model(19-OTS)installation in the Lud__eg TubeWind Ttunnei.

a. First-Stage Configuration: _zont View i14

b. First-Stage Configuration: Pear View ll5

c. Second-Stage Configuration: Front View ll6

d. Second-Stage Configuration: Rear View ll7

9. Typical operating data.

a. Model ll8

b. Tunnel ll9

lO. Vidar doz_ acauisition end plato..... 120

ll. S_4E nozzle orientation.

a. _ithout Gas Temperature Probes 121

b. With Gas Temperature Probes 122

4

ii_RODUCT!0_

Not being a conventional rocket launch vehicle, the soace shuttle

experiences complex heating and pressure conditions in its base regions

during first-and second-stage ascent due to solid rockez booster and main

engine p!ur_e interaction in the presence of the surroundir_ airstres_z.

Since these heat transfer _nd pressure conditions cannot be adequately

defined by existing analytical methods_ _h_v_.__must be determined

experimentally. _ne experimental daza _!! assist the design of zhei_.a!

protection in the space shuttle vehicle base regions.

_nis investigation, Test iH75, was _dert_en to measure heating

rates and pressures and to determine gas recovery temperatures in the

base regions of a scaled model of the space shuttle vehicle __th o_oiter

sm.dSRB firin_ rocket engines simulating p_'_me recirculazion _nd

impingement in an altitude environment. Forty-two runs were obtained at

Mach 3.5 and 4.5 with various altitudes and various model parameters

simulating n_erous shuttle first-and second.-stage flight trajectory

conditions. The model parameters included angle-of-attack, nozzle

gimbal angle, and SP_ chamber pressure. The results of the investigation

are presented in this report.

5

PLOTS'i%{BOL _,_,U_i01_C D_IETION

Tunne! Parameters (Freestream)

M _ _tACH .Machnumber

PALT altitudepressure,psi

P:_ PS static pressure,psia

Po PO sta@nation pressure, psia

Re REB Reynoldsnumber,_/_

T._ sLatic temperature, oR

To TO stagnation temperature, OR

/_ absoluteviscosity,!b-see/ft2

Mode! Par___eters _-.

ALPHAorALPHAB angle-of-attack,degrees

ELEVON CONF. inboardelevondeflection,degrees8EI

SEO ELEVON CONF. outboardelevondeflection,de_rees

? S?_ and S_4_Enozzlez-i._.:oalpitc-'_e_ng!e,degrees

Y SP_ and S_,fEnozzlegimbaly_,rangle,de_rees

Pressureand Heat Transfer?ar_eters

CAL oscillographcalibration,mV/in or V/in

DF-_ measureddeflectionon oscillograph,inches

GAIN systemgain

Kb _hin-film gauge calibration _ "_" __S_._S__lV__y, OP-_-siO?

K' thin-filmo=augesensitivi%rcorrectedforabrasionand normal,,:ear,ohms/°F

6

PLOTSY_[BOL _,£_,!0_C DEFI_U!TION

r_s_u__and Heat Tz_-nsferParm_.-eters

P PRESS absolutepressure,osia

p_ transducer pre-ru_ __mozen_ pre:ssure, psi

• pq c_ heat transfer rate, BTU/ft--sec

qp analog q-meter proportionality factor

Rb thin-fi!m gauge calibration resistance, ohms

"_- thin-fiLm gauge circuit _ resistance, olLms

RT thin-fiLm gauge measured pre-ru_n resistance,inc!udin_ line resistance, ob_-s

S pressure transducer calibration sensitivizy, mV/psi

Gas Recover}" Temperature Parameters

A wire cross sectional area, cm_

D "_ire dis.meter, cm

h convective heat transfer coefficient, cal/sec-cm2-o K

hc h corrected convective heat transfer coefficient,cal/sec-cm2-_<

k wire thermal conductivity: cal/cm-sec-°K

_ire length, cm

qc heat inout to the _re from the =_ ca!/sec

e. heat due to current flo-_, ca!/sec"J

c heat conduction to wire supports, calisec-k

q_¢ heat loss by radiation from the wire, cal/sec

7

PLOTS'£_BOL i'_FD!Oi,_C DEFINITION

" Gas Recovery __mo_r_o-_u._=_Parameters (Continued)

qs heat accumulated in the wire, cal/sec

qw{ heat gained by radiation from the gas, cal/sec

Ro :,ire resistance at To; ohms

Rw measured wire resistance, obm.s

TO initial wire temperature, _{ (20°C)

Tr gas recovery temperature_ oK

Trc Tr corrected gas recovery temperature, OK

Ts _rire suooort__t_mo_r-_ture_..__ , OK

Tw _rire t_mperature, OK

T-w me_u wire temperature_ °K

X distance aior4 the. _-__.e, cm

_,_ R-T curve fit coefficients

7 par_mmeter_/'IQ_ -!1cm

7T constant

_o wire resistivity at To(_ o = RoAi_), ohm-on

Subscripts

i_ 2 denotes long and short :tires

8

CO_GUP$.TT ONS iI_ESTiGA_D

The model ccnflguraz!on for Test !H75 _._'asa _.O_.-sca!e version of

the space shuttle integrated vehicle. Designated !9-OTS_ the model

employed short-duration, rocket firing techniques to simulate the vehicle

rocket p!m_es during ascent. Zne space shuttle main engines (S_.:_'s)

burned hydrogen and oxygen =_o_s, and the solid rocket boosters (SP_'s)

burned a solid propellant (_[B-30_6B) to simulate either first-or second.-

stage rocket plmmes at one-half z_all-scalechamber pressure.

_ne integrated vehicle model consisted of the orbiter, external ....

(ET), and solid rocket boosters (SP_'s) designed to outer mold line

vehicle 5 specifications.

Orbiter

The wing, vertical tail, and body flap s_mulated planform, contour,

_nd thickness distribution. Deflective split e!_vcns_"_.____simulated on

the wing. Inboard elevons deflected +5, +!0, and +!5 degrees; outboard

e!evons deflected -5 _ud +5 degrees. E!evons remained fixed _hrcughout

Test IH75 at +i0° inboard and 0° outboard. The rudder on the vertical

tai! was not simulated. _ne body flap remained fixed in the ncmina!

position (zero deflection).

The base heat shield was divided into four segments to facilitate

_imisalsmgle changes and to provide easy access to the instr'<mentation.

Nozzles

SS_ and SRB nozzle internal surfaces were Teometrically duplicated.

Lkternal surfaces were smooth except for one extra S_,[Enozzle which

9

CO.-'TFIGU__%TI0}:Si!FIEST!_GATED (Continued)

• " _ _ '_ _ :!-7simulated the external natbs_nds; the n_o_na nozzle _:as used in the Tr-

SS_.iElocation during gas temperature probe rtuns. _,_.,£Eand SPJBnozzle

walls were structurally thickened to _zithstand nozzle heating.

Both SbD4E a_nd SPB nozzles had gi_oaling capability. Gimbal angle

blocks defined specific pitch end yaw nozzle displacements. :_£zen

required, each gi_oal block rotated about its central _xis to simulate

various gimbal configurations; all gimba! blocks were c_s__._d to

nositioned at 45-degree intervals around the circ_mference, i_ull

position for the q__ _ and SRB nozzles :zas as follows:

Left and Right SRB's: ._cn = 0, Yaw = 0

#i S_.!E: Pitch = !6° up, Yaw = 0

"2 _0°and #3 SS_,[E: Pitch = _ up, Yaw = 0

For both S_,IE and SRB nozzles, deflections were as shown in Figure !.

r__._o non-firing So_ nozzles were provided _ith the model for

simulating engine-out ooeration._ A!tho_h the two non-firing _n_.... l_s

could replace a_ny of the three firing nozzles, they were not used for

this __es _ progrem.

OMS nozzles were non-functional. _ney were simulated internally

and externally at their "stowed" ascent position which is six degrees

pitch do'_m from null and seven degrees ya'_routboard from null.

Externa! and Suamort Hardware

External and support hardware on the orbiter, ET, and SRB's _.zere

_ nard_z___ on the ET_ consisting ofnot simulated exceot for the aft supoort " •_

i0

F _

CO_FIGU?ATi0_:S iIJUIESTIGATED (Continued)

struts, cross beam, diagonal cross strut, and L02 and LH2 feed lines.

These hardware were simulated to scale but were not detailed or capable

of carrying support loads.

Support between the orbiter and exter_.al tari_ _¢as provided by e_n

adapter which contained propulsion supply passages, autovalve control

passages and instF_entation wire passages. The adapter also provided

a mounting surface for _he orbiter _ing.

__ne SRB's were supported at the center of the external _- by

mountir_ pads. A small strut also attached just aft of the SP_ nose.

%_nemountin_ pad provided for ignition gas passage to the SRB and a

transducer installation to monitor chs_oer pressure.f-

Model Suooort

A thin-blade strut was motmted to _. _n_ bottom of the exte_a! ta._2<.

ihe strut was bolted to a base fixture "'__,__cnwas rigidly r.otuntedto _he

floor of the Ludwieg Tube Wind Turmel receiver t_-_l<. %_nus, the model

was mounted upright jus+_ dowustre_m of the nozzle exit. Model ar_gle-of-

attack was determined by the bolt hole patte._n at the struz/base fixture

interface.

Nomenclature

Nomenclature for model 19-CTS was as follows:

Component Definition

B64 _uselage body

C16 canopy

ii

Comoonent Definitionw

E63 elevon

FI4 body flap

MI$ OMS pod

N92 OI_Snozzle

N94 S_ nozzle

V23 vertical tail

W!29 wing

$22 solid rocke_ booster

_uo solid rocket booster nozzle

T33 external tarE<

_.ese components of _ne soace shuttle vehicle are identified in __i_u_.s

2 and 3.

Dimensional Data

Dimensional data for model !9-OTS are presented in Table !!I.

Model D__a,_-ings

Further description of the model including model drawings can be

fotund in Reference !.

Propulsion SysZems

(Orbiter)

The orbiter propulsion system consisted of hydrogen _ud oxygen

charge tubes, a fast.acting bipropellant valve (sutova!ve), hydrogen -__nd

oxygen venturis, an injector, a co_sustion ch__mber, and the S_ gi_oal

12

CCi,_iGU_ATiONS T" m- _ (Continued)

block/nozzleasse_olies.

The chargetubes ;€erearrangedspirallyinside the externaltank to

supply hydrogen and oxygen at approximately 3000 psia through the auto-

valve to the venturis. _nen the autovalve opened_ the _ases _rere

supplied to Zhe ventur!s at constant conditions for the w_ve time of

the charge tubes. The hydrogen charge t_oe, bein E larger, ;:as !coated

in the front of the external tank. The oxygen chsrge _ube, in the back

of the external tarH<,_as separated from the hydrogen charge tube by a

cavity used to route gas iir.esand wiring from the orbiter to _ne model

strut.

The autovalve is _o_oneumatically ooerated_ Distort .,_oe__ valve , _.o

solenoid (Va!cor) valves, when ener{ized, emitted _._5__.p_es_'o_-_..........nltrogen'"

(approximately3000 __sia)to chamberswithin the autovaivefor op_n_...."_=o

or closinT. S_,'_nozzleflow time_¢ascontrolledby Zhe relativetime

betweensolenoidvalve operation.

_ne venturisooeratedunder choked_I --_o_, conditions. _Vney were

designed for an O/F ratio of 6.0. Separate venturis are used for two-

engine and three-engine SS_LE operation to simulate the proper mass flow

az each condition; only three-engine S&ThE operation was simulated for

Test IH75.

_ne injector _,_ascomposed of t_elve doublets designed zo impinge on

a di_neter equivalent to the cc_oustion chs._ber area mean dia.-.eter.

Doublet holes were of equal size and angled _o balance the radial

13

COI;_GU._&?!CSTS=',_ ..............

momenz'_.- of the h_Tdrogen and oxygen streams.

T_.ecombustionchamberprovidednecessary-vol_me for _he gases to

mix and burn. It was commonto all three S$b_Enozzles A pyro_echn_c

ignitionsourcewas locatedin the chs-mber.

. l_ne SSbIEgimfoalolock/nozzle assemblies_¢erelocateddo_,nstre_____of

Zhe comfoustionch_ber. The nozzleswere scaledand conzouredinternally.

(SolidRocketBooster)

_acn solid rocketbooszerconsistedc? _ propellantno!def,a.n

ignitiongas system_a diaphr_m, and a ziF:oa!b!ock/nozzleassembly.

SRB flow "_'ascontrolledby the s.mountof solid propellantused; pro-

pe!l_ntthicknessdeterminedthe burn time _¢hi!epropel!s.ntsurfacearea

determinedchamberpressurelevel.

__nepropellantholderwas a cylindricalcasingwhich fit inside the

S_RB. Solid propellant(=0.050inch thick)"€asglued to a thin a!tLmintum

sheet (=0.0!iinch thick)and rolledinside the holder. Solid pro-

pell_ntsurfaceareasrequfredto producethe desired -_"c:_....oe. pressures

are listedin Table IV. Bo,_._ends of _., p._owe___n_ 7lo -.holderwere capped

to enclosethe holder duringinitialpropellantburning: a solid cap at

the forwardend _nd the diaphra@mat the aft end.

An ignitiongas compositionof ethylenee.ndoxygenfilled each SP_

just prior to i._nitionto providea high-energ_rsourcefor rapid i_nition

(<5 msec.) of the solidpropel!anY. I_nitiongas pressure$_asnominally

1_.5 psia. The nixture:€asnominallyO/F = 5.$. A pyrozechnicsource

14

in each S_RB nose ignited the gas which, in turn, ignised the prooell__nt.

The diaphragm was contained in the aft orooellant holder end cap.

It consisted of thin sheets of Mylar, 0.040 inch total thickness, sized

to burst at slightly above the desired chamber pressure.

The gimbal block/nozzle assemblies were scaled and contoured

internally.

%_ne solid .orooel!a_nt,.A_-B-30_B, was _oClass B _',o]osi_e_.._ . _'_o_

_anetioned by rapid combustion ra_her than detonation. _ne burnir_g

rate was a function of pressure, temperature and hu_r.idity.

15

INSTRUMENTATION

Heat-Transfer Gauses

Thin-film heat-transfer gauges (References 2-4) were employed for

the measurement of model surface heating rates. The sensing elements

are thin (order of 0.I micron) platinum resistance thermometers fusedt

onto the surface of pyrex substrates. The thin-film heat-transfer gauge

operates on the principle that the film thickness is much less than the

characteristic thermal diffusion depth for the short duration of the test

event. Thus, the temperature gradients and heat capacity of the film are

negligable, and the instantaneous film temperature can be said to be

equal to the instantaneous substrate surface temperature.

The resistance elements are coated with a dielectric film (i.e.,

MgF 2) which provides the following beneficial characteristics: (i) it

affords mechanical protection for the elements, (2) it improves electric

stability of the elements by sealing against the ambient environment,

(3) it provides electrical isolation from ionized gas flows, and (4) it

provides higher absorptivity to radiant heat flux than can be obtained

with uncoated surfaces. Loss of gauge response due to the presence of

the coating (approximately one micron thick) is negligible.

During operation, the temperature-induced resistance change of the

platinum element is sensed electrically. For those gauges that were

recorded directly on oscillographs, the electrical signal was fed to an

analog network (known as a "Q-meter"), which converted the indicated

surface temperature in real time to an instantaneous heat-transfer rate

16

by employingthe theoryof linearheat conductionto an infiniteslab

(References2 and 5). '_.is conver.sion is applicableover a wide rs_ge

of test conditions, if proper accountis taken for gauge resistance

changesdue to erosionand variationsin the physicalpropertiesof _he

substratewith temoerature.

_n__were recordedon _4 tape, t_For the heat-transfergau_es_" _- --_

voltage signal proportional to sL;rfaceZemoera_urewas recorded. After

a Zest run, the ta_e,€asplayedback, and the signalswere fed to s_ua!og

'.<-meter"net,corks._ne outputof these _-=,e_z=_'_.... was then __e_,a__'_'_on

a_noscillo@raDh.

_^,otypes of heat-transfergauges,,Tereemployeddurir_the test:

standardand radiativegauzes. ?he physicalconstrue<ionof the two

zauge types is similar, ni_qeends of the platinumsensingelementare

electricallyconnectedto the back of the substrateby silver film.

depositedon the Pyrex. T.qelead,;iresare soft solderedto the silver

on the back of the gauge.

StandardGauge

The standardheat-transfergau_e consistsof a platinumfilm fused

onto the surfaceof the Pyrex substrate_¢hich,in turn, conformsto the

local contourof the model. This gauge is sensitiveto the entire

convectiveheat flux, as :eel!as a portionof the radiativefl[_. _ne

____ountof incidentradiationsensedby zhe ga_e is a functionof i_s

spectralgosorptivity_as well as the spectralradianceof the energy

F_

17

INSTRUMENTATION (Continued)

source.

Radiative Gauge

The radiative heat-transfer gauge consists of a standard gauge upon

which a thin coat of aluminum black has been deposited. The coated gauge

is mounted within a holder and isolated from convective heating by a

synthetic sapphire windor, which has excellent transmittance in the wave-

length interval of interest, and also protects the relatively fragile

black coating. Essentially, radiation gauges of this type have a uniform

spectral absorptivity of about 0.85 over the 1 to 6_ wavelength range.

Pressure Transducers

Model surface and tunnel pressure measurements were made using high-

frequency response transducers (References 2 and 6). These devices

employ lead-zirconium-titanate piezoelectric ceramics as pressure-

sensitive energy sources and include integral field-effect-transistor

(FET) circuits for power amplification and impedance matching. The

complete transducers are typically 0.37 inch in diameter by 0.23 inch

thick. Units with nominal sensitivities of 2000 mv/psi (0-2.5 psi

range) 150 mv/psi (0-i0 psi range), and 50 my/psi (0-i00 psi range)

were used. Typically, transducer sensitivities are linear to within

±2% throughout their respective ranges. To provide acceleration

compensation, a second integral, but pressure insensitive, diaphragm/

piezoelectric crystal unit is wired in opposition to the active unit.

This design reduces acceleration sensitivity to nominally 0.00015 psi/g

18

IiJSTRD%LF_%_fATI0_,[(Continued)

and 0.0004psi/g,respectively;for the !ow-rsr4_eand high.-rangetrans-

ducers. In order to minimizetemperature-inducedeffectson the trzns-

ducer dianhragms,copperheat shieldswere installedto provideline-of-

sight shieldir_from radiantor hot gas sources.

Propellantflow passagear_dcombustionchamberpressuresin both

the orbiterand the BS_{'s,Jeresensedwith comm,_rc_a!, fast-response,

+_o _ _ used forpiezoelectricpressuretransducers. PCB ....n.duce.,were

___sd.ce._ were used for the corn-propellantflow passa{es. Kistier_ ......

bustionch___oers.Protectionof the transducerfrom the hot com:oustion

gases _as providedby a thin layer of R_I'''_-_over the diaphragm,a heat

shield,and a deviouspath orificearrangement. Appropriateimpedance

matching of the Kist!er transducers was _provided by ex_erna! cn_._....

romplifie rs.

Gas-TemperatureProbes

Gas-_emperature probe (GTP)measurementsin the base regions of the

_-"_ recoverytemperatures. The gas--temperaturemodel were used to d_.1__ gas

probe is a thinwire resistancethermometerconsisting of two, thin

platinum -i0_o rhodium wires, approximately ! _nd 2 zm long; mo'_nted

_ _ "_ _ _ __r_parallel on the tips of four needles positioned __c_ra_noiy. :_ _

resistancedue to the rocketplumeheatingenvironmentis relatedto the

wire temperatureand then used to solve the thin _.W.reheat balance

* Kistlerinst_"amentCorporation; Clarence, _ "_._e_York and PCB Piezo-tronics,Inc., Buffalo,New York.

** Room T_emperature V_uicanizing rubber.

19

......_.....r_.._.:- (Conzinue<._-,_,_ .__'_.'..._' ._'_--_ C_

equations to oroduce t_o tumkno:,ms:gas recover2r temperature and

convective heating rate. The two wires allow independent measurements

of the flow field heating environment for simulzanecus solution of the

heat balance equations.

qTne gas-.temperature probe was mounted in a holder designed to

oosie_ion the two wires O.lO inch to 0.50 inch _-_,_ the model surface and

to allow rotation for more direct exposure +_othe flow; wire position was

mainzained at 0.25 inch throughouL Test !H75.

Wire dis,meter varied wizh location on ___._emodel. Initially,

2.54x 10-4 cm diameterwireswereinstalledat al!=_s=...._e_er_u_2°_ _P-

locations. This size "_,iresurvivedthe model _ _ = "__r_n=,out the return

wave from the Ludwieg Tube Wind _q_unnelreceiver tar2< en_ wa!l destroyed

the wires on the external tan/: probes. Su'csequently, zhe ET _rire

diameter was doubled (5.08 x 10-4 cm).

_a_niron-consts_utan ':TypeJ" thenzocoup!e was momuted in the tip

of one needle on each probe to monitor probe temoerature d....._ model

firing.

Further description and procedures for _he gas-temperature probe

c_u be found in References 7, 8_ and 9.

Instrumentation Locations

Pressure, heat transfer, sm.dgas-temperature probe locations on

the model are sho_,,-non _.gures ha through 4t. __._ instz-_mentation is

stu_arizcd be!ow and itemized on each figure.

2O

_"a,-_a,_-_.J,.£2J.,-'_.-.,.v,±: k v.,OJ.*,,..1o._eL,. ,/

Standard heat-transfer gauges IS8

Radiative heat_tr_sfer _,_'_ _,-"

Pressure transducers 33

Gas -temperature probes 7

The instrumentation nt_nberingsystem used on ._._u.us ha through at is

summarized in Table V.

instrumentation on the model actually used for Test iH75 is

categorized according to ins_rtumentationconfiguration in Table V!.

21

A short-duration tube ",rindttunne! (Lud_riec tube) (Reference i0),

provided aerodyne_mic flow about the test model to simulate specific

regimes¢f the Space Shuttlelaunchtr__jecto_y.-migure5 depictsthe

__c_h_j and identifies its main components.

in operation,the test gas is initiallyloadedinto the k2-inch

die.metersupply tube and containedby a mylar diaphragm located .justuo-

s_re_ of the nozzle. To initiatef!o_z, the diaohragm is cu_ by me-

chanical means. A centeredexoansion__Tavethen ___p__e_-__--. _ upstres_min

the supplytube and acceleratesthe test gas to a stead:fvelocity, t_.e

__asexpendsthroughthe nozzle into the initiallyevacuatedreceiver

tar2<(SeeTable i). Mean:¢nile,the expansionwave in the supplytube

propagatesupstreamat acousticspeed. %Thenozzle supplyconditions

remain constant,and f!ow is steadyuntil thatwave, reflectedfrom the

upstreamend of the supplytube, returnsto the nozzleinlet. A

schematicdiagr_.nof this operationis sho_rnin Figure6. For the

60-footlong supplytube, steadynozzle inlet conditionsare maintained

for approximately90 r.i!liseconds(ms)when the test gas is _nbient

temperatureair or nitrogen.

The test gas.,expe_ndingthroughthe nozzle into the receivertank,

providesthe desired_,mbienttest conditionsin the free jet test section

at the nozzleexit. __netest flow continuesdo;_streamin the receiver

tan]:at high velocity,unti! it is broughtto rest when it encou_-_ters

the receivertank end wal!. The incomingtest gas developsa stagnated

22

!EoT FACILITY DESCRi_-_T!-01_( Con oinued

volume at the end wal!, which continues to gro': in the unconstrained up-

stream direction. A shock front (i.e., the interfacial boundary bet_een

the incoming high velocity test gas and the stagnated gas) thus

propagates upstream __util it encounters and (usually) breaks do_. the

_o_. Prior to test-test section conditions est_olished by the nozzle _

ing, flow bre_do_m time in the receiver ta_n]_was estimated to be

approximately equal to the supply-tube wave time for _he external flo-_

conditions of this program.

For some of the test _ans, _ne supply-tube gzs charge was b _

during its residence in the charge tube in order _o effect a more

reasonable simulation of the shuttle flight trajectory conditions. Strip

heaters_ covered _ith high-temperature insulation, _ere als__buoed

u_iform!y on the outside surface of the tube. _ne heating system

provided the capability of raising the _a!! temperature _o 600°F.

Separate "on-off" temperature controllers_ _¢ith ad_ustab!e setpoints,

were used to control the lor_itudinai temperature distribution. Cne

effect of heating the gas in the supply t_oe _ras to reduce the time

during which steady pressure was available at the nozzle inlet from

approximately 90 ms for ambient temperature gas to about o5 ms for gas

at _O0°F. *

That is, becauseof the ._.l_nersound speed in the hot gzs, ....expansion_ave velocityis greater.

23

_ST FACiLiTI DESC?_PrflC[[ (_o_c:__=s)

To maintain_ zhe.._o_=-rtunstreng<h and inzegrit,f_of the mylar

diaphragm, a water cco!ir._ system consisting o-,_ internal and _x__n_l

jacket coils _ms installed at the diaphragm station. Pre-rtun gas

temperature in the portion of the supply tube just upstres_m of the

diaphragm was consequently reduced to 300 to '400°F. Although _'__D.-, S

environmentproved suitablefor diaphragmsu_,_ivabili_y,i_ also

produced an axial temperature gradient in the supply tube gas charge.

Tnus_ as the supply-tube gas passed through _he nozzle and exi'anded into

.'_=........test section, +'_ =_o_!_otemperature varied during the early portion

of the test time. Tt _'as constant during the ...._ _±_e the data were read.

The Mach 3.5 a_nd 4.5 nozzles, fabricated of glass-reinforced poly-

ester resin, were contoured to provide _niform, parallel test section

flow. In order to comply with existing facility length constraints,

the final four feet of the theoretical full-expanslon lenten were omitted

(e.g., see Figure 7). _ze resulting man,imam free jet test rhombus

diameter was somewhat smaller than the nomina! five-foot exit dis_meter

of the nozzle.

24

Installation

_ ,.,,._ uori_ht "sosition : -- dcwnstre_Model !_-C=Swa_ installedin _'_

of the nozzle exit plane (seeFigure7). _e mode! sat atop a thin-

bladed strut _¢hichwas insertedinto a base fixturerigidi4_ attachedtc

the receivert_/< floor. Model angle-of-attack was determined by selec-

_ _ s.... ,, o_,__ ._.,.,...m._einterface.ting the orooerbolt hole oatternat the +_,_-"_ _ ....

Model instr£mentationwirir_ and propulsionlines _,:erercu;ed

through a shroud, attachedto the traiiim_ edTe of the strut, to the

lower b_se reg_onof t:'_-_-_'_ _....._ " __ _u_. Propu!sicnl-'_-,=:were then rouzed

thro,m_ha oressurebu_[headat the receivertar!<wail. Once c,'tsa:_e

the lines extendedto isolatedsources(K-bott!es)or to " _ -- _

in=_,rtm, e.,_,__,!o.. -_ires were soldered to a natchhoard a_ the base of' the

strut. Tum.nel w_.r_._=_-_r=loved___ the inst___entation signals fro_: _:'_=_

natchboard to the annroDriate data _ _ _-_ ...... ;.r.-_l=_ a_qu_s._.on_ _ems....... enreute

to the data acquisitionsystems,the -_riringp_ssedthroughsealedbulk-

head fi%ti._sat the receivertar_kwa!l and througha s-_itchingpc.he!.

Controlpanels for regu!ztir__as flo-.rto Lhe model propulsion

systemswere locazedin the controlroo_...Gases requiredto operatethe

model were:

Oxygen - orbiterchargetubes and SP_ igniLion

Hydrogen - orbiterchzrz-etubes

r-u.:_.. • • ' •-_.,jlene - SRB "_gnmz_on

He!item. - orbite:_ __.ndET ieah checkin_

25

orbiter cold flow Fans, charge tube

purging, _d SP_ leak checking

Front and rear views of the first-and second-stage model configu-

rations installed in the Ludwieg tube ;_ind tunne! are sho_ _.in Figure o

lnstrt_mentation Calibrations

T?_e calibration methods u_ilized at Ca!soar. -__.........described _ __..__.i_--"

in References __through 4 and 6, alonz wm'-_ _he theoretical consider-

ations from "';-',.,.._,c..,_ __-_',_,_.__are derived. Ca!ibr_tion records __.re-Tainr,_ined

a_ Caispan. However_ _he followin_ cor::.entsare _op._,,.__-_ ;_-_-_"" rescect

to their application to the test.

Pres sure

Prior Co the start of the test prosra:z, all oressure transducers

used in the model were _oneu:zatically c._o.oT'___ea_ with a series of steo

pressure inouts covering the anticipated rom.ge of usage. _ie voltage

outout var_az!ons of ._ue transducers were ._71"g linear within -_.

_i_eKist!er pressure transducers used for _.o.._'_-_....on-c.__.._._o__

. d_ ,e_4ca I l,rnressure measurements =core _ ..... _ calibrated orior to the test

program by means of a high-pressure pneumatic calibration system.

Linearity was ag._"_,t?-oica!!v =ze!l ". _-_,_.....n the nomin__.!+_:'.bandvld_h.

Heat Transfer

The standard calibration procedure for a thin-fi]_n "_.__o-tr__nsfer

- . _ ._S_= _-._e !Sgauge is exo!ained in detail in Reference 3 Tts _ _^*_ measured

o_ three temperatures in order to obtain the gauge's .e_oer_zu _

26

TEST -'_ _0_ (_onv,lnuec)

sensitivity K =]R/AT. The temperature range is nominally 70° to i50°F.

Gas.-Temperature Probes

Prior to installation in the model, gas.-temperature probes were

calibrated over their operating temperature range to determine resis<s_nce

changevithwiretemoerature._Calibrations",...'erealsoreauired_-_I_o,r_~__....._._

repair or following the test program to determine changes that could

account for data sm_omalies.

Recording System

A comolete_ gain calibration of eac? osci!!o_raph ....,_.crc_,._'__-channe!

wi_h its associated conditioning amplifier _Tas performed prior to the

start of the test _ _- Routine _ ,_ _p_c_. checks d....n_ the course of _he

test program, disclosed no appreci_ole variations (i.e., drift or

fluctuations ).

Operating Procedure

._qu_.ed simultaneous realization of steadyThe test objectives _ '_

exhaust plumes from three scale S_ZE rocket nozzles, as well as frc_ the

two solid propella_ut SRB engines during the short duration of steady ex-

ternal flow produced about the !9-OTS model. After initiation of the

external flow, model operation was characterized by iinition of SRB and

Sb_,_ propellants sequenced to att__in simultaneous, steady-s_ate ol'_._.e

flow.

As a result of experience wi_h the mcdel _'_=. _u....o previoustests,

proper s2-nchronizationof the three flo-¢events(i.e.,orbiterS_._

F

27

TEST PRCCEDURE (Continued)

rockets, SRB motors, and Ludwieg tube externa! f!ow) did not or_s_

significant problems. Test runs ! through 3 were required before full

synchronization was achieved. After that, the only operating problems

were occasional relay failures, wherein igniters failed to fire.

__ _rumen _a_lon beingTest tans were categorized according to the _--_ _ _"

recorded, instrumentation configurations were distinguished by model

configuration and type of instrumentation (Reference Fable o). _ne

general r_n sequence was:

i. First--stage configuration r_ns (Instr. Config. i)

_. Second-stage configuration r_ns (Instr. _on__ _-_.3)

3. Second-stage gas temoerature probe runs (Instr. Config. 4)

h. First--stage gas temperature probe runs (Instr. Config. 2)

Test runs producing good da_a are listed in Table Ii.

Procedure to achieve synchronization of the three flow events with

the data acquisition systems was similar for all r'_ns. Gas-temoerature

_ _ o_oo_ integrity atnrobe runs recuired additional monitoring to insure - _=

the start of the ran. The general procedure was as follows:

i. Fo!lo_ng model refurbis_hment and Ludwieg tube diaphragm

replacement, the tmnnel was closed for receiver tank evacuation.The target evacuation pressure was always less than one-tenth

_ _ during tunnel f!owof the nominal freestream static o._ssu_e

(See Table I). The target pressure was not a!w_ys attainable,

especially at the high altitudes where leaks around thereceiver ta_ were of the same order as the evacuation rate.

2. Approximately one hour before model firing, the orbiterpropulsion gas systems were roughly set to the desired oressures.

Any system le_ks could be detected before model firing.

Final pressure adjustment occurred just prior to model firing.

28

-_o_ ?RCC_U_ (Continued)

3- At about the same time period, the Vidar data acGuisition s:<szemwas prepared for recording, i.e., gains ",Tereset, signal fullsp_n was verified, and signal zero was verified .... Vidar

system was continuously monitored ,_nti!model firing.

4. Approximately one-half hour before model firing, thin-fihz ga_J_e

resistance readings were manually recorded on a digital voltmeter.

5. Approximately five minutes before model firing, the ignition

gas mixture was loaded into _'_o_SP$'s. At about the s_.e ._._,pre-rtun gas-temperature probe readings, total resistance andline resistance, were recorded.

6. When time for zhe model firing, a!l model and data acquisition

systems were given a final check. If ready, zhe final step was

to load the Ludwieg tuse dr,:r_r section to the desired c._a__h_-=pros sure.

7. Following model firing, the receiver ts_nk required about thirty

minutes of evacuation, before mode! refurbishment could begin,to exhaust SRB propellant residue from the tank.

Time between runs was usually dictated by evacuation of the receiver

t_k. _o or three runs were typical for _n eigh*_-hour work period.

Synchronization of the three _ •-. _o_, Lud-_--egtube, orbiter _o_,_, and

SRB, was controlled by a series of timing relays initiated by a simg!e

pushbutton fire switch. The relays were set to first; initiate SRB

flow, second; initiate Ludwieg tube flow, and third; initiate SSME flo_,_.

S_£E flow duration was typically 60 milliseconds _,._iththe first !0

milliseconds required for flow stabilization; duration was deter_.ined

by proper sequencing of the autova!ve opening and closing pressures.

SRB flow duration was determined by orooel!ant _7_""__._c_ ....s (=0.050 inch);

_ " • _Ou milliseconds with the first 30 mi!!i-total duration was <_plcally __

seconds required for flow stabilization. Ludwieg tube flow durasion

29

_,._.,_"_Rr'r'_URE(Co...... a__)

was as described _n the Test Facility section: typically 90 _ I_._- _ _

_o_ _r_vefor _mbient temperature driver gas and 65 milliseconds for .... _ _'-

gas; Ludwieg t'doe flow stabilization was typically less than i0 milli-

seconds. Tt_nensynchronizing the three flows, SRB flow ....__m,n_ was most

_'_,!__c__,o_not because of the relatively long stabilization _ime but

because of its effect on the r_ceiver tank environment. Flow _-='_'"

time, described in the Tesz Faci!i_y section, was significantly

decreased due to the mass of the SRB flow adding to _he stagnazed _o!_me

-_=-.... from the _ _- _ tan/< end wa!l. _....r_c___e .... _, data had to be recorded.... rz_no

_ur!ng early SRB flo_before f!ot:breakdo_nq.Pressure...... _ -_ at

or__,._ao..m.the Lud_,_eg tube nozzle exit p!_ne determined when flow " _' ,-

occurred. Flow breZ:do_m varied with SRB /- "__.:amo__ oressure and Ludwie_

_ube flow conditions. "4aximum operating conditions with Yodel !9-OTS

in the Ludwieg tube wind tur_el based on the f!ow breakdown orocess are

oresented in Table VIII. Typical model sm.dt'_nne! operatin_ data are

oresented in Figures 9a and 9b.

It should be noted at this time _-__._ static pressure of the Ludwieg

tube flow at a simulated altitude is one-half of the actual altitude

pressure. Actual altitude pressures were de_e__nined from Reference i!.

,___n the model S_,!E and SRB uropu!sion systems operating at one-half

full-scale ch___oer pressure and the Ludwieg tube wind _u_nnel operatin_

at cne-half actual altitude oressure, the scaled S_%_ o7.... flow field

was duplicated.

3O

TEST?ROCEZURE_n ......_:;

Mode! refu_oishment between runs consisted of mode! configuration

ch_es, new SP_ propellant, and new SRB and _SI.LEigniters. Model

configuration changes _.rereusually S_kE and SRB nozzle gLTfoal a._zle

changes. Fol!o_-ing propellant a_d igniter replacement, an SRB ignition

...._as leak check _rocedure insured that the ne'_ orooe!lant "__._o ;_ere

installed _ -= .l-_or_c__y. Loss of ignition sas durini a i-_nwould cause

SP$ misfire. To leak check, nitrogen was loaded into the pro_i'o--___--:

holders at aooroximate!y 30 _osia. An acceptable _I=_:.....r_._e......._.= 0.2 osi

per minute. For a good prop_llan_ holder installation, -'_-_.__.was ccrmmcn.,

there would be no le_< during _he first minute.

Data Acquisition

Both oscillographs _nd an _-_i-Multiolextape recorder system :-;ere

used to record test data. A total of 128 ch_n-=_--........ were -_'a11"...._'_ during

the test. However, since the total nmYoer of model measurements _,.mstoo

large to record simultaneously, four different insz_n_nentation set-ups

were used.

A total of 62 data chsmmels were recorded on 5 twelve-or-fourteen~

channeldirec_-w-riting_light-beamoscillozraohs,_employin__I_-___a.-.c._e-_ers

having a flat frequencyresponseband}W,dth of 0._00 Hz. A char_ speed

of 32 inches/secondprovidedadequatetime resolutionand frequency

resoonse. _o ty_es of conditioning_olie_e_s _=,"_ff_ _,._ __ _ , ..__l,_a variablegain

from i to i00 or ! to 1000,_orovidedthe ___o]ieication__ necessaryto

drive the galvsulomezers.

31

TEST PROCEDURE (Continued)

The FM-Multiplex tape recorder system was a portable Vidar system

consisting of 12 tape tracks with 6 channels each. 0nly eleven tape _

tracks were available for this test program to comprise the remaining

66 data channels. The Vidar VC0 amplifiers provided system gains of

0.40, l, 3-33, i0, 33-33,and lOO. To provide additional amplification,

separate pre-amplifiers with gains of 1 to i000 were connected in

series to the Vidar VCO amplifiers. Full-scale input to the Vidar tape

recorder was 1-volt. The standard procedure was to use the pre-

amplifiers and the VCO amplifiers to boost the anticipated instrumen-

tation output (heat-transfer gauge or gas-temperature probe) to 1/2-

volt for input to the Vidar tape. For data playback, two tape tracks

(12 channels) at a time were patched through a q-meter circuit (see

Data Reduction) and output on to a fourteen-channel, direct-writing,

light-beam oscillograph. Playback amplifier gains were set to provide

1-inch deflection for a full_scale 1-volt tape signal. A schematic of the

Vidar data acquisition and playback is presented in Figure lO.

Of the 128 channels available to record test data, from 90 to lO0

channels were used to record model data. A summary of the model data

recorded for each instrumentation configuration is presented at the end

of Table Vi. Channels not used for model data recorded the following

essential information:

1. Model operating pressures (propellant flow passage and combustionchamber)

2. Model timing events

3. Tunnel operating data (pressures and temperature) "-_

32

_ST PROCEDU_,_ ('_ " "',_onLLP.uecl)

A s_mna_r of she aama recorded by the V_dar _nd cs__!!u_-p._ data

acquisimion systems for each mns_umen_t_n confisuration ms presented

in Table IX.

Signal conditionir_ for the Kistler pressure transducers was

provided by external charge amplifiers. Signal conditioning for the

PCB pressure trsmsducers was provided by a !IOV multi-channel power '_t

built specifically,for the transducers. _:e power supply um.itsupplied

22V and l_-mAcurrent excitation for each transducer. Being ---o.i_

sensitive, the pressure transducers did not require additiona! ___pli-

_._on.

_nin-film zauge signal conditionin_ consisted of circuitry _,;iththe

gauge connected in series -_;_ _ ....• ,....:.,o !OK-ob_._series resistor _nd a _'3-orm

coupling caoacitor_resistor. Excitation voltage for t_.._c__,_'_ -,as,.,_OV.

_,._n-_, gauge, _:,e current _¢as2.rl,,,_.For a nominal lO0-o_m '-'_: -_ _ _-'_ circuit _ _

_,__ul__ o__x _ecor....All _,__ _ _ _-__n,._-z_L_gauges recorded on the Vidar _'-, • _, l_- +_e _ _=_

system,and -_sc_.-l_s,"_ _--apns'required _nplification.

Gas-temperature probe signal eondizioni_6 was provided by a 9over

supply panel _fnichallowed the current to be adjusted to match the probe

wire size. Tr.epanel supplied 15VDC excitation to each probe. __-hrther

details of the power supply panel are given in Reference 9.

SSKE nozzle position and inst_"amen_ationorientation depended on

the use of gas-temperature probes. Without S_s-temperature probes, the

.,'il ,,?_ and _2 SS_._inst_menzed nozzles were used -n .....positions 1 _nd 2

as sho_,-nin Figure !la. _;ithgas-temperature probes, the hatband nozzle

33

TEST PROCEDURE (Concluded)

was added, and all three instrumented nozzles were positioned as shown

in Figure llb. The figures are viewed looking forward along each nozzle

axis.

Data were reviewed immediately after each model firing to:

i. Verify satisfactory model operation.

2. Verify sufficient data and their integrity.

Oscillograph records of the tunnel and model operating data were examined

first to verify model operation. Then, all Vidar data were played back

onto the oscillograph and along with remaining on-line oscillograph data

were examined to verify data integrity. All model data were reviewed

after each test run.

34

..... RED__._Oi_

Test Conditions

_ne Mach 4.5 nozzle ;€as v___o_ated prior to Test IH75 and found to

provide satisfactory flow a_ the design i,lachnumJcer over the pressure

ravage of the tests. Because the Mach 3.5 nozzle had not been previously

calibrated, this _s done prior _o the present progrsm, and the results

are stummarized in Anoendix D. The average test section Mach .:__o___o_,used

in the data reduction, was 3.'_4.

Thus, test section static oressure and static temoerature yore

computed by:

_ 3.484 4.5

P-_ "01341 Po .003455 Po (psia)

T_ .2917 To .1930 To (OR)

where Po and TO were the average nozzle stagnation conditions measured on

each run during the data acquisition _ime. _ne respective simulated

test altitude was determined from a pressure equal to twice the calculated

static pressure (PAST = 2 P_ ) to accev_nt for the 1/2 reduction in the

combustioncnamoerpressure. The altitudes_ _ = _ _'_' " _ _o.r_s_o.._h_oZo the oressure

PAST were found using the 1963PatrickAtmosphereTables (Reference!l).

The test sectiontunitReynoldsnumber,derivedfrom isentropicf!ow

relationsusing nitrogenas an idea!gas, _Tascalculatedby usir_ the

expression

Po 1 --ocRelft: 4.il- (i)

35

where the viscosity_ for nitrogenwas based on

_ 3.46 x i0-7 {'£-_-J2_T\__/: T_ + 19 (!b-sec!ft2) (2)

"_ithT_ in oR.

Pressure

Al! of the pressuretransducersemployedduring this program7:

operateon a differentialbasis in .......• z__._ _ney sense .._ change bet'Jeen the

7_ ai__c _oressureaoo!ied__Lo the model during_he van and the n_e....n __o_o___..=_-

pressure. Aeeordinglv_the receiverrand<pro-run_s_7"_p --=-....

adied to the measured pressure ckange for a17 _.-_-_ ...._-- ._=.._._..... e]:Dcsec:Lo L:qe

_n_,_o.u_..... For the SRB s, however,the initialignitiongas

o!-essureof lo.5Dsia _zasadded to the transduceroutoutto derivethe

absolute_oressure.Absolutepressures;:erecalculatedaccorSin__,_

Equation(3).

= CAL X D_. + PR__ (_s__)-_ (3)" s x GAIN

_i:ere

CAL = oscillograph calibration (mViin)

DEFL = measured deflection on o.c_lloo_a__._dueto trsmsducer output (inches)

S = transducer calibration _ _--""_;_ _,, -"/ "

C<_iN = system gain

P_ = tr_--nsducerore-rmm ambient oressure (psi)

36

DATA ...."....- ....' "......."

Im._.ethin-fiLm gauge is _'_resistance thermometer "'_{-_.__._responds zo the

local surface temperature of the substrate. _ne_ classical _'bae.ry_of heat

conduc._ion in a homogeneous body is used to relate the surface _emmerature

history to the raze of heat transfer. Due to the considerable effort

required to convert _ _ _ -_--" _ _:c_r,,.,_e.....r,_,t.... im_ _-_ _ _ into ecuiva!en_ heatin_ rate

histor_s, an analog " _' _" •negro..,.,referred to as a "c-_-_r,;' has been

deve!ooed to c_._ve'_zthe temoerature _-:'_':_direct!v into a hea_ ST,_-,_-_

real time for oresentstion on the osci!io_raph (Reference 3). All t:!in-

e4_ =oug_ hea_-transfer data for this study were obtained _hrou_h _':e

use of q-meters.

For the heat-transfer data recorded directly on the osc__7_l_5._-_a_..o,---

each channel was equipped with a q-meter. _.e heat-transfer gauges

recorded on the _4-Mu!tiplex tape recorder system were handled some:That

differently. _e outputs of the thin-fiLm gauges (which are proportional

to the su, f_e_ temoerature of the gauge) _..rere,eco_d_d on the _4 _a:e.

After each tess run, _.'__aoe was played back through a.u analo_ c-meser

and the signals proportional to heat-transfer rate were ,_co._ed cn

oscillograph.

Signals from the q-meter analog circuit, proportional to the heat-

transfer rate, were converted to heating rases by the following ecuations:

M Kb x (RT - RL) . Io_' = ( o_-_s! -_) ('_)_o

37

K' = gamze sensitivity corrected for abrasion randnorma! we__r

Kb = calibration sensitivity (ohms/°F)

Rb = calibration resistance (ohms)

RL = circuitline resistance (obzns)

R_ = measuredpre-rungauge resistance,includinglineresistance (ohms)

30o._'o,-,x K

qp is the analog q-meter proportionality factor _o convert gause outpu_

in volts zo hea_=n_ -ace

• q_ x CAL x D_L ,,,,-,q = - _BTU/'ft_-_sec)GAIN

where

= heating rate

CAL = oscillograph calibration (V/in)

DEFL = measured deflection on oscillograph due to zaugue output;

the deflection may be directly recorded through _ c-mezer

or played back from the Vidar 5hrough a q-meter (inches)

GAIN = system gain

Recovery Temoerature (Gas-Temperature Probes)

Gas-temperature prob'e data reduction at the test site was minimal.

Information were presented for calculating @auge output in mil!ivo!ts

on!y for comparison during later off-site data reduction az P_,[_H_ Inc.

To facilitaze data reduction by _ITECH, the Vidar _4 tapes containing

38

gas temperature probe data were first digitized at the Rockwell inter-

national, Los An_e!es Division D_ics Laboratory. ?*o time frames of

data, 270 msec/frame, were digitized at a rate of 3000 sar_p!es net second.

_ne time frames covered the .oeriod from 1GO milliseconds before _,,eSRB

ignition signal, T2, to kCO milliseconds after. D__l__z_d data tapes

received by R_iTECH_ !nc. were converted to n-= -_e..__neer_.= units, reformatted,

and used as outlined below zo calculate gas-recovery temperatures and heat-

transfer coefficients.

Gas--recovery temperature data reduction procedures, in general, re-

main unchanged from those used for previous impulse base heatir_g tests.

_ese procedures are doc'a_enzed in References 7 and 8. For test _175,

however, there were improvements to the data reduction progrsm used for

calculating gas recove<r temoerature. ?nose imorovements are detailed

in Reference 9 and outlined briefly in the remainder of this section.

Previous data reduction recuired simu!tm_eous solution of the

como!ete heat ba!ar.ce equation for two thin wires. The equation is:

qs = qj + qc - qk - q_¢ + qwg (7)

where

qs = heat accumulated in wire

a. = heat due to current flow-j

qc = heat inout_ to the wire from o-s

a. = heat conduction to wire supports

q_¢ = heat loss bv_ radiation from _'_.___

qwg = heat gained by radiation from gas

39

A r_ _. \u:_±n R_UCTiOU (Con_inusd j

_.-Js eauation was non-linear in two urc<no_._.s,T_ and h, and ...._'_"

a mznerica! iteration scheme via a cor_pucer code called S_BE 4 to obtain

solutions. Lmprovements were made in Reference _ where a linearized

semi-closed form solution to the wire heat balance equation orovided

initial esti_ates of the recovery temoerature_ and ___ea_-_r_._o-_"_ _-_=_ coef-

ficient for the ._on !.....r =t_m_r.._l technique,thereby savin£_ consider-

sJs!e data reducLion time.

_zrther modifications to the linearized semi-closed form solution

have produceda ccmp!etelinearsolutionwhich sjreesvery well ;'ich

r-- • . _ne resultsare nluchacreresultsof tl_encn-iinearnumerica!_ec.....que

• %"4 _rda_a in much less data reduction time; spec'__,cal!_, gas-recovery _emoer-

ature snd heat-transfer coe__.-cle._._-"=_"" _ can now be obtained as a function of

a___._edtest time, insteadof a singleaveragevalue,_-11_'"_'_.,.:._.more-_'--_-'l

analysis.

_ _ O_o_ data has sho_m _'__oerience with oreviousgas temperature__^".......

mosL heat transferassociatedwith the _.'iresis due Zc convectivehe_t

input and conduction. Eliminatingother t}"p_esof heat, Equation7

simplifiesto:

qc : c_:<

UDS _iuU_l_ :

- T,;): -A Tw. (?)aX_

where

4O

h = heat transfercoefficienz

,p___diameter

Tr = gas recoverj._e_pe_tu_

Tw = wire temperature

,__r_cross section?.tea

k = wire therma!conductivity

X = distancealong wire

AssLL,_ir_k does _o-_ vor_:__ "4ithtemperaturesm.ds_.._o___u__.._._"_...."'_.....for :_,

4 dX2

Equationi0 can be transfozmledinto a simplehomomeneousdifferenti__.l

___ua_.on'_(Reference_12):,rhichhas the solution:

cosh -<"./ .'-.L.)/ _ )

where

Ts = wire supporttemperature

= wire !engZh

To obtainthe _ver=_ge-_iretemperaturefor a finite length_,rlre,Equation

ii is integratedover the wire length.

{_, = zr - (zr - Zs)_ (LJ%"--/'_'D) (_-_)

Solvingfor Tr and _ _n- _ = '_nse._...eDare_meterT h!kD,

-mr = (_ _) ['_- Ts t_ (£ 7 ) (13)- ta=_ (_)

Equation 13 is _n ex_!ici_ expression of finite length single-wire kent-

ins with two "_uk,_o_n_s,Tr and h. _,_o distinct equations csm be wri%ten

for the two different gas-temperature proce wire !er_Zhs, denoted by sub-

scripts i and 2, and solved simultaneously _o obzain an equation of only

or.e'o_qkno_.r_h.

2x- = - Tsta .

For practical use of the precedins equations, Y r.ust first be ob-

tained from Equa+_ion !4. From Y, h is calcu!azed and used in Esuation 13

to obtain Tr. ?arsar.etersTs, _w, _ used in Ecuations 13 and 14 are ob-

tained as follows: Ts, the wire support temperature, is measured by an

iron-constmntan _hermocouple in the tip of one of ,_= _s-_e._p_r ....e

probe short wire support needles. _.7, the averaie vire tempgrature, is

calculated by Equation 15.

_._ -- .% [1 + _(_,,_- %) + Z'--N_,-- -%) (15)

",,"mere

Rw = measuredwire resists_nce

Ro = -_-ireresiszanceat temperatureTo

2 _°KTo = 20°C = 9_

_, _ = R-T curve fiz coefficients

_a_%_:.Vireleng_.x, _, is calculated by Eouation 16.

A1.853xi0-5 ohm-on for Plating-- -._ ?hoditu_.i(16)_O = _O "; =

z wire

42

where

_o = manufacSurer's stated value of resistivity at To

With all parameters known, 7 is still not directly obtained -_rcm

Equation 14 due to the hyperbolic ftunctions. .'4_nefficient meshod forq

oo_alnlng accurate values of 7 is kno,,m as the __bonacci series search

routine .......It is an inte_Tal elimination s_or _ _-:_._,_,_oa"",',.n__n_"sets uooer__

and lower botunds to em initial heat transfer coefficient estimate

(hinitia! = ! x 10-2 ca!/ca-2 - sec - °K) and then ?roceeds Zc rsduce _he

inte_"_al-:_"'_ _o oDtimtu_- value occurs'_-_ _ P-',',_--__- _'_reached

if the final value is equivalentto the upper or lo-¢erbounds,i_ becomes

the ne_,¢inizia!estimate,and the orocedureis ._e_ed.

) i.e. h _.ndT_, must_ne final solutions to Equations 13 and .__, , .

satisfy the follo_.;ingboundary conditions; if not, She solutions are

considered non-convergent.

Tr > Tw! > Tw2 > Ts

Tr < 4000_1

i x 10-5 < h < 1.0 ca!icm 2 sec - _£

As gas temperature increases, the no._-!...e___terms of Zhe :_.re [:eat

balance equation, ignored for the preceding simolified solution, cause

the linear zas recove<r temperature to diver_e from the t_ae non-linesr

solution. Correction Equations 17 s_nd !S are applied to the linear gas-

recover/ temperature _nd heat--transfer coefficient so!uzions to account

for non-!inearity.

43

DATA REDUCTION (Concluded)

Trc = 4.6805 x 10-7 Tr3 - 9.4521 x 10-4 Tr 2 + 1.6682 Tr - 152.02 (17)

_c = 2.8598 x i0-I0 h4 + 6.1589 x 10-7 h3 - 5.0279 h2 + 0.13456 h + h (18)

To use the simplified linear equations, the following assumptions must

be made:

i. The gas-temperature probe wires are at a steady state heatingcondition.

2. The convective heat-transfer coefficient and gas-recoverytemperature are identical for both wires.

3. The wire supports do not significantly disturb the flow inwich the measurement is made.

44

_ne basic Test _475 reduced data consisted of steady-state heatin<

rates,pressures,_d gas recovery_ .-.... ,"__. _ne da_a ,.-e_e......o.....

at -_time correspondin_ e_ szeady mode! _ "_"_ "'-_"_ " "" _" 7 ..... "_=_

and ttmne! fic;;. _ressure and heating rate raw data were hand measured

at the steady-state time from the osci!lozrcch traces and entered into a

comouter oro_r__= for f._n:._,lreduc_ior_. _Lccvrccy of ,_hese data can most

_..e_o_..e_........G-as-7.enderatu.relikelybe direct]</relatedto the hand ....._.......-

probe daza -,-ere-_a,_-_,=_,_.===j_-_'-_-;_ccm.'uter._.._.'-o'_-_=_-_____.._._ in =:1_

ccmouterprograms,..........n_ brieflyin the precedingsectionaridouZ-

lined thoro'4ghl_,in Reference9, allowed-_i_reresissance,wire temoer-

ature, recove_jtemperature,and convective-e=._:.._cceffici tc -_

_ I t_= ',_==e time _Io_s a!lc?redo!otted as a function of ,__de_ firing ............

visual evaluation of the overall __o-_emo_.oj=-- "L='°_'-_'J-_'e_orobe response --_nd

insured that steady-state conditions existed.

Vidar and o___._.n-^__"_-_2' data _u____'_v--=-.,_.eh___.!persdhy ..... .,__.:.......

noise ratio. Ds.taon osci!!ozraphsand on Channelsl-k! of - = Vidar

systemseemedto nave the best quality,_tn Lne noise noL ...........D_ ....

steady-statedata level;however,data recordedon Channels1-4! of the

Vidar sj'"-_e...._ _mDlovi_=__ ..oCalspanamplifiers_ere in error as discussed

later. Data on Channels4._-¢oof the Vidar system_..___._,"_-__._incor

._p!ifierswere of the lowestquality;in general,%he noise and data

levelswere of the s_me order.

._._e.completionof the test prozr__,__ noted L.qatsome of the

45

RESULTS A!_DDISCUSSION (Continued)

data recorded on the Vidar FM tape system exhibited a droop indicative of

a limited DC response. This was traced to the use of amplifiers having a

100K ohm input impedance with heat transfer conditioning circuits that

had a 1 Mfd coupling capacitor in the output. _uis resulted in a system

time constant of only O.1 sec. for Channels 1-41 on the Vidar _4-Multiplex

tape recorder system. The effect of this time constant on the output of

the q-meters was analyzed, and correction factors were determined and

applied to the data. The analysis and correction factors derived by

Calspan are presented in Appendix C.

A discrepancy in the magnitude of the gas--temperatureprobe data

recorded during second-stage configuration runs 39 - 43 tends to dis-

credit these data. Specifically, the recorded wire resistances produce

wire temperatures and recovery temperatures t_ce as large as expected

and twice as large as any previous data. Oscillograph playback data from

the Vidar and digitized data from the Vidar FM tape compare in magnitude,

which points to the Vidar input as the problem. However, investigation

did not prove that the Vidar input channels _¢ereincorrectly spanned or

that the gains were in error. Thus, the gas-temperature probe data were

evaluated two ways: (1) using the actual recorded data referred to as

"literal data" in Appendix B and (2) using one-half of the actual recorded

data referred to as "literal data + 2" or "input data + 2" in Appendix B.

Analysis of the results of both types of data, detailed in Reference 9,

did not conclude that either set of data was correct.

46

RESULTS AND DISCUSSION (Concluded)

Tabulated source data are not supplied _-iththis document but are

available through the Rockvell International, STS Aerosciences Departmentd

as shown in Appendix A.

Oscillograph traces of the raw data, includlr_ Vidar playback, are

also available as shown in Appendix A.

Gas-orecoverytemperatures and convective heat transfer coefficients,

derived from the gas-temperature probe resistance and thermocouple time

history data as described in the preceding section and Reference 9, are

presented in Appendix B. The data were extracted from Reference 9. Both

literal data and literal data _ 2 are presented. Steady-state gas-

recovery temperatures and convective heat-transfer coefficients are

presented in Tables B1 - Bh. Figures B1 - Bh show an example of time

histories of the gas-temperature probe data. Gas-recovery temperatures_

plotted as a function of simulated altitude,are presented in Figures B5 -

Bll. Convective heat-transfer coefficients,plotted as a function of

simulated altitude,are presented in Figures B12 - B15.

47

_-'_EP_'TC ES

!, <uan, ,_,T., "In-"o._r..ationfor Bsse o_ ^_ ,_ __. ._e=_t,._and Heat Transfer Tests "_

the 0.0225 _ _= Space .Lj-L;Tcin the-oca:_ Shuttle P!tu_.eSimulation Model "_ _ '"

_,IAoA/_a._sp,_nLudwieg l_be Wind Tu__me!(Z_7_A) " SD76-SH-OI43,Rockwell International, Space Di_-ision,dated April ii, 1977.

2. Bogdan, L., "Instrumentation Techniques for Short-Duration Test" ual_oan Report No. %_{-O30, Buffalo, _T=,,York, dated_cilities,

!?o7.March, ":

3. Bogdan, L., and GaWoeroglio, J. E., "Transient Heat-Transfer Measure-ments _th Tnin-F!Ln Resistance Tnenzometers -- Fabrication endApplication Technology," Technical Report ::u_&PL-TR-67-72,CalspanCorporation, Buffalo, New York, dated June; 1967.

"Transient Surface Temoerature v ........_:- " Ca!s_4. Vidal, R.J., _ ,............e.._s, =,....Report _To.114; dated March, 1962.

5. Skinner, G. T., "Analog I{etworkto Convert Surface Temperature toHeat F!u_x,"Calsoan Report No. _0, dated l_:oO

6. Martin, J. F., _a__gea,G. R., Stevenson, L.._.v,"Ins_,_n_a__on__ forForce and Pressure Measurements in a Hypersonic Shock __muel,"Calspan Report No. 113, dated January, 1962.

7. Fuller, C. E., IX!, sm.dEngel, Dr. C. D., "Gas Temperature ProbeDevelopment and Sho_ Duration Space Shuttle Testing Support,"RE4TECH, Incorporated RTROI5-1, dated December, !_.4.

8. _-hl!er,C. E., Morrison, M. _¢.,Powell, R. T., and Levie, J. K., Iil,"Utilization of a Gas Recovery Temperature Probe on Space Shuttleo._or_Duration Base Heatir_ Model Tests 0H75 and _£39, R__TE_,Incorporated RTROIp-2, dated July, 1977.

9. Fuller, C. E., Levie, J. K., lii, Powel!, R. T., "Utilization of aGas Recovery Temperature_Probe on Soace_Shuttle €,_nor_Duration BaseHeatin==Model Tests _75 and !}{83,"._4TECH_ Incorporated RTROi9-3,dated July, 1978.

" '__ and Wilson, H. B , Jr.,i0. Sheeran, W. J._ Hend_r_not, K.C., . ."Applications of a Tube Wind LVhnnelin Suoersonic Testing/ AL_%Paper No. 69-_35, presented at 4th Aerodyn__ic _s_zn5 _on_e....c_,Cincinnati, _io, 19o,.

ii. Smith, O. _., and _eidner, D. K., :_Reference Atmosphere for

............... _ o_te__er _-4,_'T,Tma_-t,[a--s_s_Soace Flixht Center, dated _ _'_ _"_ _-_o

48

"Resistance m_o-_ Transducers," _,_etrolo:Ty12. Sandborn, V.A._ ....r.......Press, For h Collins, Colorado, 1972.

49

[£hCI{ ....._m.. To - :+ _ _U_E ?;<]},'.I[O. .-.__I_<,mn Po -_ -_o--:a_'r:_ PP!;:},g.]P£

Kft. o_ PSiA PSi__ =:: _S_A, K:-!

^ - _30 Z30 _.";:- " ' !P _'"_4.,o - _ -'.__ ,..,.g_2! ._,-_ 7.75 < bOO

!I0 ' L"_.0 _o 0.033! 27k4 _.._0'.... < _-'_'_"t

1_0 1.756 0.0231 11o2. 2.i0 % 1,.,""',.,

l:kO i.if:o o.o15f _oo l.hO < 75

"' _ I0'_ _DO 23.770 0 ....... " n..,- < ._.,.,

!_3 i -,, -'- -'_/] "151' ....

14o 4.477 o.o115 830 :.,.u=.... < 7P

!oo _o! 23.770 o.o221 k2k9 " "_

i!0 i 15.352 0.0531 ___"h!,l"_ 17.-.._'° < __'_'_._,

120 ] I0.0£8 0 _ _:_ < _:_

f/

_ " _:_k 0.023'9 !192 : .._ <!s_ o .... 7.h.< !'_0

140 -."k77 _.____ _< 800 5.02 < _:,

150 3.0k2 0.0105 5k4 ! 3.k! < 50

160 2.082 0.00719 372 i 2.33 < 3_I

_, 17o _._6 0.00493 255! 1.6o < 25I

5O

TABLE II. DATA SET/Run NUMBER COLLA.TION SUl-lrlJ\RY

SPACE DIVISION Prepared BYI "og_ No. of

/E5T .Il-/75 NORTH AMERICAN ROCKWELL CORPORATION Checked 8YI a.port No.,. , ''/ ,. ~ . .. . .001., Model No. -

1 2 3 .4 5 6 7 8 9 10 I 11 12 i 13 14 i 15;V; z- z.. LiS /" Ii j6-LE;-:':' IC'nur,\1,('~ 1( '><. : -·r··",

I

C-' 1/'1 S'/iL:J:.,<~:I r:..

b"'~$et- 10 AU.+.clc... 0<C------.___ '----

[L~(':~ I -55,.,...':;---"--'--

~~ Ca".c'j' Mc:o11/ ~ ::';1/';- ~2 :;SJI'e.-:; i-'3 j:'-""C. ..:> .. L R 5('6 ...r;r;.i3

lId....4It.. (or=-\ (\< ('t:) Cl:)~9') y -P-rT -1:> y T-' 'I 'II

C,.:OII'-) (:>:.,,.,j _:~:--f -!l ~ .P ? I

OOf 4- QTS 3.5 .3~o /00. +5 0 0 0 0 a 0 !o 0 0 0 I I~-()O ~qO , I

ooz 5 //0 I Ii II

()o3 f., /30 I I I /d5I

I

004- 7 , 4-0 I I { I005 10 4.5 fooe> ~ I i 2<70

,Go&, /1 ! /00 I007 /3 10 ~

IIi !

oo~ /4- . /10! I

I I ;

00'1 /.5 , "?o I I I :

. 0/6 I /7 /30 I I I0/1 /q ~ • i ! /{)O !I

012- I 20 14-0 I I ! I I i I0/3 2.1 ISO I I I I0/'/ 23 /(PO I I I { I! ;

0/5 24- I /30I I I ;2.co II

14-0 Y I I ' . j40' (/> 25 I ,

I I

2~ /20 i I i I0/7 +/0 i I 210

QIP 2.7 t -/0 )' -:, i I +o,q 27 / <fo +5 -s 0 -s 0 -5 0 -I 0 -I 0 I I 100 1!

020 2Cj OT ! - 1- - - ! - 3

02.1 3D /1..0 i I

022 31 ! 0 0 0 0 0 0 i I i()23 .32- /70 1 \

02.'1 33 /50 I I ;

,."I,~ 5 ~ '/ y J'{ 0 ~ t t.:J Y-I" II"" H1'':, .... '1 ~ v I ",I

)

TABLE II. DATA SET/RUN NUl.ffiER COLIATION SUl-1MARY (Concluded)

SPACE DIVISION P,.pored by..

'age Ho. 0/

/E:~T IH75 NORTH AMERICAN ROCKWEI.L CORPORATION Check.d e"'l a.port No. I, ... .. o • JDole. Mod.1 No.

1 2 3 .c 5 6 7 8 9 10 11 , 12 I 13 14 I 15

D",-la5<+ 0(~ Z-l.. L::- C; 11"1 IdAL- Ii /c;.LL=-S !C-~o"l, •.<: -r;~~.~ ~ V4"~~ :.J:,c_ I ~.

'k?,,- Co".cj .10 AU1~<- "I 5:>I'IC "250-;,.le II3 :J:/'.'~ L~('i3 R5t:'d I ~~:::~~ ~r::i3

.ra....-/ •.f,... M~ <. 01="\ (.1< .('t) O)~9') -py- p--y -p y I T' 'I P 'I ;;-'... ,r.) ~<'".-lolll~

02~ 35 aT 4·5 70 13-0 -t-5 0I

/ !SOO ::20 0 0 0 0 - - - - - -"

027 : 3&. 14-0 ..,..10 T t: II

02}' 37 { -/0 I ~oZCJ 3q OT GT'P /30 +5 I 4-

4-0 /40 i ; I030 I

631 41 /50 i I I I()32 4-2 /100

. !03'3 43 /70 i I034 4-4- /4-0 -5 Q -5 0 -5 0 I { I i I

Y

035 I 45 op/Grr . ! t -I 0 -/ 0 /00 Z03{.. 410 /00 0 0 0 0 0 <:) oio a 0 ;ZC;o

037 47 le.O

63~ 4-q /4-D I '/00

O::::q So J30 I tOL1-o .51 I [,00 /20 I I 2C;o

n41 52 /00 i I i Iy

.5"3 ~ /20, I I04-2 OT5 I I 't

iI :t

II

I II

II :

I ,I

I ! ,r---- -0

II

lJ1N

TABLE Ii!. MCDEL u!:,_,_0_,._m.......... _'_i=

MODEL CG._Ci,.m,Ff: BODY Bck

G_¢ERALDESCRIPTION: _ne body is to the BaselineDefinitionSpace [hu_tleVehicleConfiguration5_ HCR 200, Rev. 7 dated I0-i7-7k.

HODEL SCALE: .0225

DF_&:,_NGI'_,IBER:VC70-000002,,_,_-v'-70Baseline_,[L

Len6th: CIILX0 = _-_p---o _ __. '-=_&.D -, ,,

Ref. Len6th: OHL XO = 235-1528.3 in. __,_.I_o_3 29.032

L_--th_..=. (Z_ILXO = 2q9.5)_in. ]_q_.& =_-_,.>'_'_°

CHL Hax. Width, in. X0 = 1516.$01 2J2.7i_: _.911

.-u_, in X0 = 1516 301 : -f-

CML },Is=_.Deoth,_ in. X0 = !_3.316 _-U_._,_<_= 5.593

]_4LHax.Depth, in. XO = _o3.316 2'_.p_p _.545

CHL FinenessRatio 5.203 5.203

]]qLFinenessRatio 5.227 5.227

Area - Yt_

Max. Cross'Sectional@ X0 = !463.316 3_0.82 0.173

53

T_BLE I!I. MODEL DIMENSIONAL II_TA(Continued)

MODEL CCMPONENT: CAI_CPY- C!6

GENERAL DESCRIPTION: Orbizer 102 Canopy per MCR 1750

R1 Baseline

MODEL SCALE: 0.0225

DRAWING N_MZER: VC70-OOOOOS-q,_SD-V70

DIMENSIONS : . FOaL SCALE MODEL SCALE

Length, in., _e = 433.07°_i_to Xo = S70 236.9207 _.5_!

...... _.3!_,',_'_ _.;idzh,in., _ X0 = 59h !9L.£39£ ; _=

Max. Deoth, in., @ XO = 492 _._=:_qq07 1.323

Area - y_.2

Max. Cross-Sectional @ XO = _D-_O 45._c_ 0.02B_4

TABLE III. MODEL D_q_SIO_[AL DATA (Continued)

MODELCOL.[P0_T_NT. Eim-70N- _'_

GESTURALDESCRIPTION: Elevon for Configuration 5, hinge!ine a_

XO = 1387, E!evon split line, Y0 = 312.5 _.0" gaps beveled edges, endcenterbodies "CML"used on WI29 Ref. MCR __O0,R=_:.7, dated 10-17-74

MODELSCALE: 0.0225i

DRAWING9[uZ4BER:VC70-O0000£A

DI_4ENSIONS: '_JLL SCALE MODELSCALEArea useD for _4e computation 210.0 O.10c_z.fArea,Ft- -_oo.57 0.!0_

S_an (equivalent),In. _ kk -_<--

Inb'd equivalent chord, In. 1i6.50 _.__-i_<_

Outb 'd eouivalent__ chord, In. _==._i_ "._.___:_'_

._ Ratio movabl_ surface chord/total surface chord

At Inb'd equiv,chord '_.........

At Outb'd equiv, chord O._._oeG 0.3999

_eep Back Angles, degrees

Leading Edge 0.00 J_._,_^_

Trailing Edge - 10.056 - i0.05_

Hingeline 0.00 0.O0

Area Moment (Area v I,D\C)- Ft3 !5&O "'".- •,_ 0.0175

Mean Aerodym_mic Chord, In. _0.50 _.Olk

55

TABLE III. MODEL D_._NSI0_tALDATA (Continued)

MODEL C0_.[PONENT: _ODY FL_P (0LLfERMOLD LI_S): __'

GE_D_q_J_DESCRIPTION: Orbiter body flap vehicle _ Configurzsion, _,_CR

200, Rev. 7. "G_IL"to be used ,;ithB6g ...._ ......X0 1532.0 Y0 -12_0.

MODEL SCALE: 0.0225

DRAWING Nt_4BER: VC70-000002, MDV-70

D]_._,SIONS. _"JLLSCALE MODEL SC__LE

Area, (Total), :-t_ l_g.125 O.'Ob_

Span (equivalent), In. _ :_r-__.O0 5._,_

Inb'd equivalent chord, In. _i.00 i._23

Outb'd equivalent chord, In. 81.00 1.#2_

Ratio movable surface chord/total surface chord

At Inb'd equiv, chord

At 0utb'd equiv, chord

Sweep Back Angles, degrees

Leading Edge 3.0 S..D

Trailing Edge O.D 0.0

Hingeline O.0 O.0

Area Moment (Product of c & area), _3 905.3k4 0.0103

. . 1.___ean Aerodym._ic Chord, In _i.0 s_

56

TABLE ZI. MODEL DIM_IOI_AL DATA (Continued)

MODEL CG_PONENT: Ci.4SPODS ( n,,r -- ._,

GENERALDESCRIPTION:Vehicle _ _-" _: _ 200,., co.... _a .... .,_,, I.ICR 2ev. 7,

0rbi_er_4Spod - shor_pod.

MODEL SCALE: 0.0225

n _ _.... _70-0084!0, "mDRAWINGNUMEER:V_7,J-_u00=, _L_V-70

DIF_D_IONS: FULLSCALE MODELSCALE

Length, ix. (XOI3!! to 1511) ___'30._0 4.5'00

,.:ax.,,,,d_n,in.(Xp304,....7"_

Max. Depth, in. (-'(p304,XOI51!) 7k.50 l.J7_

Fineness Ratio i o_v 7 0_7ejj I --'i_--f--

Area - Ft-

: ,c. 'J. O_ rMax.Cross-Sectional @ :,:p 30k _.1_9 _ _

r

57

TABLE IIi. MODEL D_IOi__L DA_& (Continued)

MODELCCMPONENT:_'"J_ZZ_o - _._

GE_z2JILDESC_TION: _i= two orbiter_ ..... _- r.ozzies...... a_eu,e__,.bsyscer, are

lav_l-be!lshapedand a_=._locatedat the ___._end of zhe 0,_S.._cod, C_,!S

nozzlesin stowedpos__+_.o.._are ou_oo=._d'_-_ 9° and do_ 7° from null oosition.

MODELSCALE: 0.0225

DRAW-!_ NUMBER: V070-000002, S3-AO!2EO

DIMENSIONS: FULL SCALE MODEL SCALE?_&CH NO.

Lena<h, in.O_nbal Point to _xi_ Plane ._0.00 1.2_?O

%_nroat to Exit Plane

Diameter, in._it _0.O0 !.125

_nroat 27.77_ O.o_

Area, ft. 9_it 13.63 k O. OCt9

_n _oat t, _= 0.002 !

Gimbal Poin_ (Station), in.Left Nozzle

:<o !5!8.,3o 3k.i55Yo - %3.o0 - !.odo

'"" !!.o70Z0 4y_.CO

Right Nozzle

X0 15!8.O0 34.155YO + 88.0 + 1.9_0Z0 492 •0 !i.070

Null Position, Deg.Left Nozzle

Pitch 15°49 ' Up !5°&9' Up

Yaw 6o30 ' Outb 'd 6°30 ' Outb 'd

Right Nozzle...._!_cn 15°49 ' Up 15°a9' Uc

Yaw 6030 ' Outb'd c_30 Outb

58

TABLE iIi. MODEL DIMi_S!ONAL 'n%TA (Continued)

MODELCC_4PONENT: _2oSI[0ZZLES- i$9h

GENERALDESCP!PTION:ri_emainpropulsionnozzlesare lava!-be!!shaded

and are locatedon the aftplanesof the orbiter._ne dimensionsare

externalandnot to be scaledforplumetests.

MODEL SCALE: 0.0225

DRAWING NUMBER: VC70-000002, VL70-OOSIk4, ?_09!<_9,$S-A012i_

DIF_NSIONS: FULL SCALE MODEL SCA!__ C_ NO.Length, in.

Gimba! Point to Pz_itPlane 156._9 _.52_

Diameter, in.Exit 93.75 2.!05_

Area, ._.7_<it !S45.00 O., 3__

G....c_l Point (S_a_on), in.

Upper iTozzle

xo 14_5.oo 32.5!3YO 0.00 0.0

Z0 4L3.00 o.__

Lo_¢erNozzleX0 i_8. 170 3__.034

Yo + 53.oo + i.!93Z0 34.26k 0.771

Null Position, Deg.

Upper NozzlePitch !6°0 Up i6°0 UpYaw 0.0 0.0

Lower NozzlePitch i0.0 Up 10.0 UpYaw 3.50u_b'd 3.5 Cutb'd

59

TABLE Iii. MODEL D]2._SI0r_L DATA (Continued)

MODELCCMPONENT: VERTICAL- V23

GENERALDESCEIPTION:?se _e___cal tail is double wedge shaoed and

mounted dorsally on the aft fuselage. ?nese data correspond toVehicle 5 configuration, MCR 200, Rev. 7.MODELSCALE: 0.0__)

DRAWINGNUMBER:VC70-000002,masterdimensions.

D]]4ENSIONS: FULLSCALE MODELSCALETOTAL_%TA

Area (Theo.),ft2Plsm_form 413._5_ 0.,_J>_

Span (Tneo.),in. 315.72 7.-0_

Aspect Ratio !.6_p_- !._-'_=

Rate of Taper 0.507 0.507

Taper Ratio O.40k O.h04

Sweep Back Angles, degreesLeading Edge 45.00 45.00Trai_lingEdge _6.25 •_6.250.25 Element Line h!.13 kl.13

Chords :Root (Theo.) WP 26_.50 6.Ok!_p (Tneo.) WP 108.£7 2.k4!MAC i99._i 4.496Fus. Sta. of .25 MAC 1463.50 32.a_o_W.P. of .25 _£_C 635.52 _._Tk_0¢B.L. of .25 MAC 0.0 0.0

Airfoil SectionLeadingWedgeAngle,deg. i0.0 _J._"_Trai!ing Wedge Angle, deg. __lL.G2_ !k.92Leading Edge Radius 2.00 O.945

Void Area 13.17 0.007

Blanketed Area 0.O0 0.O0

6O

TABLEIII. MODELDIMENSIONALDATA (Continued),',I._C-- %¢72cpMODELC0MPOI_I_: "_" _

G_ERAL DESCRIPTION:The_¢ingis ihe_'_........_'_:_....]_:_t':ngdevice and ismounted hcrizcntal!y and is s_e___c about +b_._ .o1__.o_eYn = 0. A cufffairs the fusela!_eto the wing's leading edge _$TO 9hO _o lOSk.MODELSCALE:O.0225 DRAWINGNO.:DI_-_ISIONS: FULL SCALE MODELSCALETOTALDATAArea (Theo.); ft 2

Planform 26_0..O0 i._._o__""Span (Theo.), in. 936.62 21.075Aspect Ratio _._c> __.,'., _Rate of Taper 1.i77 i.!77Taper Ratio 0.2D0 0.200Dihedral An=_le;degrees 3.500 5._O0Incidence Angle, degrees 0.500 _q.i_OAerodynamic Twist, degreesSweep Back Angles, degrees

Leading Edge k5 -_,i'qTrailing Edge 10.056 10.05c0.25 Element Line 35.209 35.209

Chords:Root (Theo.) B.P.0.0. :529.24! !5.j09Tip, (Theo.) B.P. 137._L9 3.102MAC &74.8__ !0._3Fus. Sta. of .25 MAC i!3o._3L -,--._7_W.P. of .25 MAC 290.:357 _.544

,o,, I_2 4 093B.L.of .25t,t&C _'--_.-_ •EXPOSEDDATA

ft2 1757-5n 0._ rArea (Theo.), •Span, (Theo.),in.BPI08 720.6_ !_5.2!5Aspect Ratio 2.0_0 2.0_0

," ',,a" _. _,__Taper Ratio 0._> _ _i-Chords

RootBPI08 5_2.090 _c _';,Tip !.00b/2 !_7o_,_....._, _.!O_MAC 3__._o s. _39Fus. Sta. of .25 MAC _.I,4c.50 2'_.',-'5,c

.cu3 o .cOcW.P. of .25 _t&C 293 _o ....B.L. of .25 MAC -'_!.70>, 5 _'_

Airfoil Section (Rockwell Mod NASA) XXXX-64Root b/2 = 0.1136 0.1!36Tip = o. o.

D tafor(1)of(2)SidesLeading Edge CuffPlanform Area, ft2 !45._ 0.07LLeadi_ Edge Intersects Fus M.L. @ Sta 5.30.0 11.25

. .C,}, ,_Leadi_ EdgeIntersectsWing@ Sta i0_,_.,_ _.39

f

61

TA_BLE ill. I._ODELD_,I_S!01_AL DAZ[_ (Continued)

MODEL C(I_01_--h_2: BOOSTE_R SOLID ROC_ZT I,ICTCR - S2_

G_PA.L DESCRIPTION: %The BS_,i is an exter:_.a!propulsion system _,fnichis

],e_!soned_"_nd recoverable a_=_erburnout. ]_ieBSF2I's can be _e% "_-....

bished _nd reused after recover_j.

MODEL SCALE: 0.0225

DRAWING _NZZKBER: VC77-000002C VC70-O0000_\,' VCT2-O00002C

DL_$SIONS: FULL SCALE MODEL SCALE

Length, in. 17_9,60 40.2_6

Max. Width Tan__ Dia., in. !_.00 3.2°5

"_ . in. 208._0 .oo_max Depth_ Aft Shroud Dia.,

Fineness Ratio _._96 $. 5_6

Area, _.

Xax. Cross-Sec_ionai 236. _23 O.120

_._of BS_,icenterline (ZT) hOG,0 9,DO0

F3 of BSE.:nose (XT) 7L3,0 16.718

of BSF$1center!ine (YT) 250.5 5,636

62

•__BLE iII. MODEL DIN_NSIONAL _ATA (Continued)

MODEL C_ONENT: SOLID n0_F]__BoOo_LR -

GENFAqALDESCI_P_ON: SRB nozzle to nearlines to use _l_. $22

MODEL SCALE: 0.0225

D}K_WING_: VC77-000002D

D]3{ENSIONS: FULL SCALE MODEL SCALE

Diameter, Dex- in. (I.D.) 145.64 3.277Di_neter, Dex- In. (C.D.) ik7._5!4 3.322Di_ne_er, DT - in.Diameter, Din - In.

Area, Ft._ _5 "_ _'___ .c_o 0.0_

Gimbal Point (8Zation) - in.Left Nozzle

,_ _ !c03.h58 ki.92°XB - hot 1375._p_ _.l,_oYO - - 25,0.50 - 5.636ZT C00.0 9•000

?/ght Nozzle.... _l.y_oXB - cold !_3 !'5_ ' .....

XB - hot i_7_.35_ _._.,'._It.<,YO 250.50 = ="'_ZT h00.0 9•000

Null Position_ Dez.Left i,[ozzle

?itch 0 0Yaw 0 0

Right NozzlePitch O OYaw 0 .j

63

HCDEL CC_,_ClY_'Ff: _{TE3}IALT:A_5[- T33

G_--_-£_-SLDESCRIPTIOi[:Externalzai< _th sp_i,=._._nose. Dimensionsare

calculatedto the outermold line (C,_4L).

HODELSC.&LE:0.0225

DP_;_IKG I'_,IBER: VCTS-OOOOO2B __ -"'-_ _-- No .... " " - ' ,__oJ.._._ nose u,,5. .: o,_cO0-'O59a; '

D_._F2[SIONS: _P-u SCALE ::[ODFLc_,.T_S

- q-,', ' " " % --o-

Lep_th, In. ±£,p,_. aSo a!.o_±

.._-_'°".Dia. U_[L , In. 333.00 7._

Fineness Ratio ;._ _.

Area

.° _Hax. Cross-Sectional o04.c0, 0.30_

64

SP_BNOY,_!['[AL PROPNLL_'_SU__ACEAP__AC!£AMBER o_=qcv-o_ (_%CH SP_B)

29O !30

200 l0_

i_5 _-_J

i00 "_I

°

65

TABLE",T.iNSTRUb_AT!0i;"<'........

Comoonent Or 7n-< _ Actual N_mbers_ i......o_rTnszrtt___nLaLion Series Como. or ZnsLr. _lumbers

Orbiter 1 - 200 Total _zin-FiL< Gauges 1 - i!9

Radiation Gauges 12'3 - 132PCB Transducer !_°_ _ _L_7_Locations

E_<terna! Tan-'< 201 - 300 Tota! 7::in-Fi!_ Oau_es 2D1 - 22':2Radiation Gauzes =_'O - 2_

Locations

S.RB's 301 400 Tota! '_,'_-PiLm Oa'_<es 301 - _cm__o- 333

,__.di__,o_,Ga_ges _.--- _--_

_ 325?CB Transducers _,-- -

Locations

*Reference S_a_ic 501 - 600 r-_:___,___ 531 - ._7_--_

?re::sure s External _:'.i- 5].k - _i_ --_

SRB (LeftHand) _,!7

,TR:leI<T2CICOU._Ies 601 - 699 See T'Lb!s-vii for listing

.... _ 70o - 750 _"_:,:oae_ Operating .;o._.:_,_c 700Pressures Left SRB Pc 7'01

_ =_-t S_ Pc 702

0e=Vec.tvri _^.,O.- -- . - . _-i:_ ve.:.'::'_ 73/:

__._.___._r

...... 7_O_.s Temperature 751 - 799 c,roz_er 7;-= - -"2rooes Ext ernz! Ta_': 756 _-c. _ IDc,

i!,e_I/ srS'"

H_.tbandT_roz-q_ 166 !80 To_al --' "'_ "_ 7m "_"i_ 76_ li:O(Flat and contoured) (HBi-HB!5)

* D!et applicable to Test _175

66

1 )

TABLE VI. INSTil_4ENTATION COI_[GURATIONS

CONFIGURATIONOR SET-UP

i 2 3 4PA_R PARAMETER (yp,

CCMPONF_ DESCRIPTION (Y_S* 0TS W/GTP UP W/GTP

N_4BER TYPE DATASET 1-19, 35 -41 20-28 29-34IDEI_I_IFIER 42

9 Standard XOrbiter Side Gauge

i0 _ X

14 Standard X [

Orbiter Top Gauge

15 _ X

23 Standard X

Gau!_.e

Wing Upper 24 X XSurface

2_ X X

27 !' X

t

* OT,i;is first stageshutt]__:coni'i!.!iur:,I;Jon(orbiter,_xtern:l].t;_r,];,SHB)*_ Cll_ is sucom] _ta_aje ui,uttle colli'iljurui,J,,,n(orb:iter, external t_unl,)

_51BLEVI. INSTI{U]4F,IZ#ATIONCONFIGU]{ATIONA(Continued)

|.

CONFIGURATION OR SET-UP

i i 2 3 4

PARAMETER PARg/.DYI_RI ----e_o_ _ Dmcral_'ncu or_¢ _,sw/a_ oT_* ...._._}_io'r<_

ml.m_r _E m_sET 1-19, 29-3_iD nEr 35- a2o-20]:

30 Standard X

G_tu6e

31 xi

VerticalTail32 " X X

oo X33

34 x x

35 'Standard X X

Gaug e

36 X X

Body Flap 37 :< X

38 X XH

39 X X

* OTS Js fJrs_ stase slmtt]e con£'!i;uratJon (orbiter, (,::t era d 1,,_r:],, ;,]il_)

*_ UI' is secured stai_e shuttle collrJdurutior: (ofD] t,,tI', e>:b(: F_l;l ]. b:t:ll'.)

) )

" 1 ")

• TC,r | _T. r I T "_ * - " _ "'I%%BI_VI. ]LJIIFt$!],,_[rAIIONCOh_FIGURATIO}:C(,_ont:nu_d)

CC,I_FIGUI_dI'ION01}SkT-UP

i 2 3 4

I'AI_}IE'IS!IRPAIVJ,U ,_-'(,- i_ , .___O'.L'SW/GTP OT_CCMPONE%FP O,..... It]:. PICN LYI':;_ ()T _:/GT:"

Nt_.IBER TY][.: I)aTA:-_l_f 1-19, 35-4!. 20-28 °')-_4IDENTIFIER 42 '- _

43 Stand_ X XGauge

45 x x x x

Body Flap 46 X ,

(Continued)125 Badiative X X "

Gauche

139 PressL X X X

........................................... t...............................

55 Stand_ X

Left C_S Pod Ga_ce56 _ X

Left Olt_)/RCo- 57 Stand_ X X XInside Ga_ _ •

Surfaces 58 I _ X X59 Y ,.: x x ×:

(I,_is first stage shutt]._:coni'iduratJon(orbiter,,:x[._rn_] ....._" ,,1,1)_ Cil'is secondsts_zesl_uttlecon±'i,;ur,_l, ior. (orb]Let,e::bern_-it_Ln!:)

TABLEVI. INSTI[U]4ENTATIONCONFICU|{ATIOI,IS(Continued)

CONFIGUtb"¢PIOI_ 01_ SIC2-UP

ufl:.,, 2 3 4PA1]Ab1ETER PAPAI._YI_']R OT_ W/G']2COMPONENT DF._J_]ItIPTION OTSW/GTP OT

_!.IBER TYPE I_TASl_fP 1-19, 35-41 20-28 2_)-34IDENTI FIER 42

Left C_4S/RCS - 60 Standard X XInside Gauge

Surfaces(Continued) 61 )[ X

f-_ o2 Standard I X

o Gauge 'I

63 Z Xi

Left OMS/RCS-Aft Surfaces 64 X X X

65 x :< x x

66 X X X

67 X X .X

Orbiter Base 68 Standard X X X

Heat i;hieid Gauche

69 T X X_i .............

* OTS is first stage shutt]econfiguration(orbiter,extern:%lt_nk, .%RB)_ U2 is secondstage shuttleconfiguration(orbiter,externaltank)

) )

.,)

TABLE VI. INSTRL_,H_,NTATIONCONFIGUIL%TIONS (Continued)

CONFIGURATIONOR SET-UP

i 2 3 4

PArk'S,tillERPARA]._]TER OT**C(_4PONE_f I)[._]CItIPTIONUPS* OTS W/GTP OT W/G'['P

NUI.IBER TYPI.] I_TA SI'.T 1-19, 35 -41 20-28 20-34IDF,NTIFIER 1_2--- _ .............. -- ...... r

70 Standard X X X XGauge

71 X X X X

72 x x x x"-4

73 X X X X

74 xi

OrbiterBase iHeat Shield 75 X

(Continued)76 x X

77 x x

78 x x x

79 x x

80 x

* (YPSis flrststage shuttleconfiguration(orbiter,externa],funk, S}{B)_w* (YPis secondstage shuttleconfJ.gurution(orbiter,externaltank)

TABLE VI. INSTR[_4ENTATIONCONFIGURATIONS(Continued)

CONFIGUHATIONOR SI[;T-UP

i 2 3 4

PA P_!_IETER PARAMETER , , OT** f"'C(IqPONENT DI_CILIPTION 0T[; _ O[['S W/GTP OT W/,IP

NI_,IBER TYPE I_TA.%_:I' 1-19, 35-4]. 20-28 29-34IDEN%ffFIER I€2

81 Standard X X XGauge

82 X X X X

83 _X x x x

._ 84 X X X X

25 x x x

86 x xOrbiterBase

}[eatShield _7 X X X(Continued)

88 :,< x ,(

89 X X X X

9o x x

91 x X X "<

* OTS is first stage shuttleconfiguration(orbiter,externalt:mk, S|(B)_+_ (7fis secondstage shuttleconfigurutJor(orbiter,externalt_ml{)

1 ) )

TABLE VI. INST|_,II,:IgrATIONCONFIGURATIONS (Continued)

CONI,_I(]UI_d'I(dI OR SET-UP

l I e 3 4

PA_TER PA RAI4_'I_R OT_._CGMPON_ DE}JCI_I_ICION I ui,sw/o o_ W/GTP

RLI411ER TYPE I_\TA:]_P

XD£_{'I[IFIER 35-41 20-28 _ 29-34

92 Standard X XGauge

93 X X

94 x

9.5 Xbo

96 xOrbiterBaseHeat Shield 97 x X "<(Continued)

9_ x x

99 × x

1.00 ' X

130 l{adia tireGauce

131 V

* (Ii'3is first stage shuttle configuration (orhlter, external t,at:,l;,bld_)*_ Ul'is second sLage sl,uttleeonff_durutlorl(orbiter, extccnal tttltl;)

ff_BLE VI. II_STI_IIi]_ATIONCOr_FIGURATIONS (Continued)

CONYIGUI_VI'It,N OR SET-UP

1 2 3 4

PARAMETER PARAMETER O_ _ (Tf _*C(h4YONE_ DF_CRIP'FION U_S W/G'I_ OT W/GTP

li_._IR TYPE IIATASET I-19,IDF_TIFIkq_ 42 35-41 20-28 29-34

133 Radi ative XGauge

134 W :<

145 Pressure X X X X

.j 146 X X X X

148 X X X X

Orbiter Base

Heat Shield 11_9 X X

(Continued)15o ,," X X X

155 X X X

158 ' x :(

¢-_ . -162 ,..tand.lrd :_

Os_;e

163 _ X X X

* UI*£is first stage shuttle configuration (orbiter, external t:_nk, :Sld_)

*_ UI' is s_cond stage shuttle configuration (orbiter, exteL'nal t_nk)

) )

TABLE YI, INSTKt_4I;:IrfATION COI@qGURA'flONg (Continued)

COI]_XGU!W['I(',N OR SET-UP

1 2 3 4

PARAMETER PARAI-_--_ER Off,x.COMP0_ DI_CRIPTION UI_ _ 0TS W/GTP OT W//GTP.._

NII4]_R TYPE BATASL'P i-19,IDg_flFI EN 42 35-41 20-28 29-34

................... -- ....---.

164 Standard X X X

Gauge

165 f x x

622 GTP '.Knermo- X X

couple

523 xOrbiterBas__.LnHeat Shield 624 'r X X(Continued)

752S GTP (Short X X

i Wi re)752L : (Lon,; X X

Wi re )

753S (.Uhort X XWire)(I "753L I .,ong X ,'_

! _./ire)754S : (..qhort i X

Uire )75Im i' (Lo_:-: x x

WJre)

L__

* (Ji%;is flr_t _tage shuttle configuration (orblter, uxLern:_l t,:L:d;,Sldl)

_+_ _Jl':[8second a;ta,_eshuttle confl4:,;urution(orbiter, cxternz_l tttnl_)

TABLE VI. INSTRI2,1],_[fATIONCONFIGURATIONS(Continued)

CONI,'IGUI_V['IONOR SET-UP

1 2 3 4

PARAMETER PAP4_4]_ZR OTS* OT W/GTPC(_4PONENT DE}3CRIPTION OTS W/GTP (YP"__4]_'/{ _XPE DATASET i-19,

IDE_'fI_ ER It2 35 -41 20-28 29-34

Nozzle ,_Ii01 Standard X X X X

Gal._e102 X X X

lO3 x x x

"-4 _Y"o_. i01_ X X X ,_

_,c, _ ,, A k X...._ME Firing 105 _" "'Nozzles

106 X X X X

107 X X X X

t 0 . _r].9o X X X ,_

109 X X X X

ii0 X X X X

* (YF3is first stage slLutt]eeonf']l{ua'ution(orbiter, extern_l t:m]:,/DRB)e_ (YI'_s second stage shuttle coufi;!;urutlon(orb._te_',extu_'uz_lt_mk)

) )

1 )

TABI_ VI. INSTI_LnH_]r_ATIONCONFIGURA'I_ONS (Continued)

CON_GUYWTION 011SET-UP

1 2 3 4

PARAMETER PARAI_,'fER __ OT_ _COMPONENT D_SCIIIPTIONi UI_* 0TS W/GTP OT.W/flTPI_ _PE IIA'I'A._;M9 i-19,

II)92¢gIFIEII h2 35-41 20-28 29-34

Nozzle#2iii Standard X X X X

Gauge112 X X X X

113 x x x x

SLI'4EF1ring 114 X X X XNozzles

115 x x x x

116 x x x x

117 X X X X

ii[_ ,'[ X X "!1

119 _'" X i[ ]':

IIatband 166 Standard { X XNozzle. Gau.,,;eI167 I[ X X

* CcI_iS flr6t 6tage shuttleconfiguration(orbiter,externaltank,,Ul0_)w_ Uf is secondsta_c shuttlecol|l'IL4urution(orbiter,extei'nalttfllk)

TABLE VI. IIIGTITOl.IENTA'YION CONFIGURATIONS (Continued)

i,

CON_XGUIVd'IONOR SET-UP

i 2 3 4

PABAHETER PAI_'I'ER , __ OT_*COMPONENT D_CRI_ON _YfS* OTS W/GTP OT W/GTPi

Rl_ TYPE DATASET i-19,ID_an'IFIER 42 35-41 20-28 29-34

168 St_ ndard X XGauge

169 x x

17o x :<

171 X Xoo

172 x xHatbandNozzle 173 X X

(Continued)174 x x

175 X X

176 -. x x

].77 x x

178 x x

* 0%_3is first stage shuttle configuration (orbiter, external t:_nk,SI(B)*_ (71'is second stage sltuttleconfiguration (orbiter, external t,.mk)

i) ) )

TABLE VI. IIISTIR_,H_|TATIONCONFIGURATIONS(Continued)

i,

CONFIGURAT OR SET-UP1 2 3 4PARAMETER PARAMETER OTS. (yf.-x-COqPONENT DESCRIPTION OTS W/GTP OT W/G_?NUMBER TYPE DATASET i-19,

IDENTIFIER 42 35-41 20-28 29-34

Hatband 179 Standard X XNozzle Gauge

(Continued) 100 ] X X

210 Standard X

-_ Gauge

_o 211 I X X X X4

212 J i X!

213 ] X,_ternal TankAft Dome 21|1 ' X

215 x

216 X X

217 ",, X

21_!', 'I I; x

* 0_ is first stage shuttleconfiguration(orbiter,external tank, Sld_)_ (YI'is secondstage shuttleconfiguration(orbiter,extel'naltank)

TABLE VI. IIISTI_bTI]'_ATIONCONFIGURATIONS(Continued)

CON_GUI_Vt'IONOR SF.T-UP

i I 2 3 4

PAPER PARM4ETER I (YP__: COMPONERT D_ffRIIXrION C/l_* 0TS W/GTP OT W/GTP_R _E _A._mT i- 19,I

× /231 RadiativeGauge

233 i X '

234 Pressure X X X X

235 '"(DO _\o

-30 X X X X

],ixternalTanl; 626 O_? Then,_o- XAft Dome' couple

(Continued) 627 I X

OO&.o X

756_; c,'_P(m_ort x

-_:_ -I Wire)

7>oL (Long XI.li re)

757:_; (m-_ort xWi re )

• * UF.:;Is l'irt;tstage shutt]econfiguration(,),.biter,cxter,,altanl:,LIIB)•_ UI'Is secondstage sl_uttleeollflgul'utlt}n({}rbJter, ext{:rll_,ltttllh)

} ) )

1 'I ")

TABLE VI. INSTHt%II2FfA2[[0NCONFIGURATIONS (Continued)

CONI,_GUI_TION OR SET-UP

i 2 3 4

PARAMETER PARAMETER OTS. OT+_caPOmr DESCm ON W/OTP OTW/OTPI_I4BER TYPE BATASET I-19,

IDENTIFIER 42 35 -41 20-28 29-34

757L G_? (Long X

Wire)l!_ternalTank 75_S (Short XAft Dome Wire)(Continued) 75_L T (Long X

Wire)oo

F_ternalTank 221 Standard XHardware Gauge

228 _ 5(,| ..................... ,, ...............

302 Standard XGauge

303 Xleft SI_

z

Sidewall 305 X

306 X

307 I' x

* (YI_3is fir6t stage shuttle configuration (orbiter, ext.ern,_l tank, SHB)

UI'is secondstage shuttleconfiguration(orbiter,externalttmh)

TABLE VI. INSTRL_,IEIg2ATIONCONFIGURATIONS(Continued)

CONFIGUIWTIONORSET-UP

i 2 3 4PARA]4E_R PARi_4E_R _f**CGMPONENT DESCRIPTION (_9S* (YfSW/GTP _f2W/GTP_FtI.[BER TYPE ]]ATASET i-19,

IDEI_IFIER I|2 35-41 20-28 29-34

327 Standard X

Left SRB Ga]_e

Sidewall 328 X(Continued)

329 X X

_ 308 Standard X

Gauge

31o x

312 x x

_r

313 XLeft SIKB Nozzl_

and Shroud 314 X

315 X

316 X

324 Pre ssure .',_ ,_"

325 _ X L____XX

* (Yi_Sis first stage shuttleconfiguration(orbiter_externaltusk, SIhB)_ UI'is secondstage shuttlecbnfiguration(orbiter,externalt_t*H;)

) ) )

• I

TABLE VI. INSTRI_4ENTATION CONFIGURATIONS (Continued)

li CONFIGURATION OR S_J_-UP

i 2 3 4

PA_LMETER PAP_._ER _f**CGMPONENT DF_C[LIPTION OTS* (YI'S_':/GTP OT W/GTP

NI_4BER TYPE I_TAS_I' 1-19, 35-111 20-28 29-311JDEIt_[qFIER 1t2

317 Standard XGauge

318 "_^ X

319 X XDeft SRB Skirt

Curtain 320 XOO

fOo_9 GTP Timrmo- Xeouple

759 S GTP (Short X

T Wire)759L (Long XWi re )

Standard ,'33 69 87 70Gauges

Sununary Radiative 7 i iGauges

Pressures 9 I0 I0 i0

* (YfSis first stage shuttle configuration (orbiter, external t_m]:, S}{B)

*_ OT is second stage shuttle configuration (orbiter, external tank)

TABLE VI. INSTRIn,Hg_PATION CONFIGURATIONS (Concluded)

CONFIGUII/d'ION OR SET-UP

l 2 3 4

"PARAMETER PARAMETER UPS* OT* _C(14PONENT D_CRIPTION OTS W/GTP 0T W/GTP

N[_4]]ER TYPE ]]AT/SET i-19,IDENTIFI KT_ 1,2 35 -41 20-28 29-34

GTP 'l_ermo- 7 3couples

GTP (Short 7 3Wi re )

Summary GTP (Long _ 3

co> (Continued ) Wire )

Data 99 i00 98 90Channels

* OTS is first stage shuttleconfiguration(orbiter,externaltunk, gliB)(YlIis secondstage shuttleconflgurat_on(orbiter,extez'nalta:,k)

_ne_oeoupleNumb er Loc ation : _,_'pe

622 Gas Temperature Probe (GTP) 752 (Or'oizer) Iron-Ccnstantsm- _

(_e J) i623 GTP 753

i624 GTP 754

626 G_ 756 (-Lxternal Tar_)

f_0_7 GTP 7_7

6_8 c-__e758

629 G__? 759 (Left SRB Skirt Curtain)

85

TAb_ V!II. l,,"&_'<_,_%t".-O,_Eu"'_" _ _I9-OTS OPE._&'_,--!!TGCCI_!T!OI._S

PRESSURE S_,_W_ATED ALTITUDE

290 psia 130,000 ft.

200 psia IkO,O00 ft.

i00 psia 150,000 ft.

86

r ..................

!I[ST_RD_4_,[TATICg ,_-.... _ "COh._'_-Um__!0hDATA ACQUISITION SYS_S ! I 2 3 4

OTS lOTS .:,,_/'GTPCT OT b'iGTP

MODEL DATA:

_-IDAR:

_': _2 63 44Heat-Transfer Gauge _nannels _

Gas_Temperature Probe _namne!s -- 21 -- 9

Total Channels Used 65 63 63 53

OSCILLCG_HS:

Pressure Chs,nnels 9 I0 i0 i0

Heat-Transfer Gauge Channels 25 27 25 27

! Total Channels Used 3k 37 35 37

I- (I) TOTALMODELDATACH_,_,_IS 99 i00 95 9,3

TU_D_L Ai'_MODEL OPE_<TIi[GDATA:

Vidar Channels I -- I !

0scil!o_raph Channels _ 24 25 25

(2) TOTAL OPE_%TiNG DATA CHA_._LS 27 2£ _o_"I __c_

_,_SED C"Jl_,__LS.

Vidar -- 3 2 12

Oscillograph 2 ! 2 --

(3) TOTAL U}YJSED_L_LS I 2 4 4 12

TOTAL_sTDATA_=_mLS[(J_)+(__)+(_)]I1<-8_S _'__"°

i

" !,'O _,'_,

.........L

P

87

NOTES: I. Olmbal angle deflection is away from null.2. Positive pitch is nozzle trailing edge dovn.3- Positive y_ is nozzle trailing edge left.h. (P) is the absolute magnitude of the angle.

5. (Y) is measured counterclockwise from the positive ya_ __x.i_.

.Y

ht

' ZB =0

TB = 0 YB = 0

YO =0

YT =0

%qF_ LOCKING FORWA!_D

.__ur_ !. Gi_oa! _ug!e definition.

88

63

- Figure _. Orbiter vehicle.

89

~S22

~----=::::::::::======:=:::;:;;:::=:=-::::- - - -

------=::::;:======~=====-.:::::-- -:. -:.. = =- --- --

1---

~T33

Figure 3. Integrated vehicle.

90

0 Tot,_l he-at transfer gauge

Radiation heat transfer _auge,_

Q I1ezo-Llectrie transdncer location

A Reference static pressure tap

0 Gas temperature probe

I 2 3 4 5 6 7 ASOIB 9 121 Jl_| i_--" [_ = ]I00

................ O O • O .O. -.O.....6 O ......O ®-O ..................z = 3i"5

-- i 135 , I0

<_ 75.o) . .'J25 •9754

,'(/I, = . 10 .20 •30 }10 .50 . ()0 •70 . bO <'0 o_:;

i0 Tota]2 l¢_dJ.ut:!cn[! i'I'(._Ssl!rL:

2 Re ['c.rence

a. Orbiter Side

Figure 4. Instrumentation.

5 To cal

b. Orb Jt,er Top

l,'ig_rcIf. Contiml1_d.

.90.................../

/

/"

i

/ 2 _.70...................................

/ '/" "/." /

/" " ./ ./__. ,,.•50............... .-..:._................................-y .......................

Ylbl2............. ........... C..............................O...................! ............._,, 0,__,

//'" i i

7 Total1 Radlatlon

i,'] ,9__'(: -If. Co_lt] nl,,::d.

.95

\

\I

\,

\\\

\

\\

\

\

'-.

23o

-,.60 --

x/c =:: .15

.45-Y/b2"

.110\ .60\ \

I-----------------------~----------

\-240--·-.\

\

d .~Jing Upper ;:';Ul'l':lCE

Fi~;url; Ii. Continueu. 6 Tota.1

,1

34

Tr2.i lir~~ ::;dge

.40z/b

6 Total

/

II'"-.---- ,--- -----.-... _- .- 0 _--~/-_f----- .20

/

/31 /'32 //

/ /"-------- .l~I '

/ °1I,/ /

.80 .90x/c

290

X/L = .50 .85

X/L LOCATICI,S HATCH 'IHCSE OFGAUGES OK 'lliE ms POD

e. Vertical T~il

Figure 4. Continued.

95

41

---- .5G2 (M:J)... ... _-.2Hl---..

(r-l~; )

IlOl'l'c(~

VI1';W

--~l .7n,l (MO)

1.00 (1-1:3) I

Jt .. 04.503

\31

_-..L__ -._.--' ~_ ... - ..-------- •. -.---•. - 0 (50 .~-----.---

41 124

TRAILING EOOE

12 Total 32 Radiati on 2

PressureReference

f'. BOlly FlapFigure h. Continued.

A,,k_----TICALTAIL \ h \ k \ \ h ". \ \ \ h \k \L__EKALF-'_'AYBET_E-II_s6$s_ O O __V.T. & c_3PODS.._...----

_i_i.---

sl os: s_ s4 Yo = 680 -- 0 0 ---

"TOP VIEW

.85x/_ = .3 .9

•5 .7

,_, !

4Y 48 49 $0

3

SIDE VIEW _//_/

I0 Total

-- LeftC_:SPodoe

Figure h. Continued.

97

5 To t,'.l1

h. Lei't (_:_S/T_CS- Inside! ;',urf,:+:ee:_l,'Jg1_re h. Contirl_ed.

) )

@ GAUGES ON OUTER

NOZZLE CONTOUR

1420Aso6

\\\

" _

\\

6 Total

3 Pressure

i.. Left ¢_qf;/i_(';i, Aft f;uri'aces 2 Reference

Figure 4. Continu_d.

RadiationPressureHef'erence

221

----

1,

127--@

1,/2---1

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

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

-4--. ----._-_ •.

~---------------------------

126®

--'---

-----~=---j-'-"'--\~

I-'oo

,j. Right C\.ti/nCfi - Ins:i de Surf~lCeGFigure If. Continued.

2 Radiation

Cg °-' • •k. Righb OMS/RCS - Aft _,uxiacesFigure );. Continued.

«lIH

0011 lSI

IS'•

OI5J

019

OUO

690~..

SOI""O'®IJO

"0

L Orbiter Base Heat :jhieldl"igure h. Continued.

92

o16

o11

33 Total5 Radiation

14 Pressure5 Reference3 OTP

- 8/9 L [ _IS GAVGE CI_LYCN NOZZLE 1

-7/9_-

5/9u___--_.'219T,.__ I

° i

t ,o,,o,i

h

19 Total2 Pressure

NOZZLESi & 2

No___. _ozzle _ I

159 _ PressurelOl-llO 1 Total

160 2 Pressure111-119 2 Total

161 3 Pressure513 3 Eel.Press.

\

NOZZLE 3 I Pressurei Reference

c, =_._ Firi_ _ozzles- Figure _, Continued,

103

/

/

FO[-6'IAI_I)< > Air'.[' / / "

171 168

I--' 17, 175 173 /670 "%67o .................................. 0 ................ (9 ....... !6___.........................4>- 17;

17e " -- - ....... -O-- - 0 .......... 15 ° PIA__,]]_179 leo TP_C],.;

• Gauges l(i_Iand 171 face aft

" Gauge 176 faces forward _ _

• All other ga_-zes are perpendicular

to the nozzle surface Oaug,, numbers 166- '_i_0 u.,_'_..synonymous with _]au_e

15 '.['oral nm.hers HB1-HB15.

n. ]latband Nozzle

li'igureJ_. Continued.

) )

_01 202 203 204 iO_ 9 "_

...... :0 ....... _....... 0 ........ 0 ........ 0

}..a .................................. : ................................................................. l

_ O 135° I_'R_i_IO VI,',R_ICAL O O 236o .............. " _o5................... ei,o6............ 2o7 " 2o,. ! i

.......

I

.;[ .9X/I:p o .o

= .,_ .Jr.85

• i ._ f0 _o _,._].1 l_ad_ation

]o. Lxterna_Tarfl_Sidewalll_.gurc_t. Continued.

f 2 515_L 234 215 232

l O----e ® 0 [] _ 0 ® j

RgI:_.2L].OI20Z I

021o //

9 ToZal3 R_diation3 Pressure3 Reference2 GTP

o. LxternalTa_< Af- DomeFi@ure _. Continued.

106

•-t .................................................... El_ ................................ _"

VI}'M I,OOKING I;'OR%IARD

ii [£otu].

q. ]'_.tcrna].TankHardwareFigure _[. Continued.

f

326 327 328 329 330

I

g 3 .92 _.._

30, 9 00 FROM V]_:RTICAL302 303 32, 304 30s 306 307_-'oo°................. ? " 0 ........... 0 .... ® ...... 0 0 0---- 0--- --

f

X

= ,195 .l3 .60 .65 .70 .80 .90 .95

L_ SIDE VIEW

L1,.'I,TIIANI) ltOOK]t;'.l.'ONLY

i£ Total1 Radiation

l,_igure}t. Cont_ nued.

'-or. R.H. SRB c.'\l.l'

45a---./ :

s:rRCUD~

'!SF-OAT

FL/2~~~ J2t,..- A

1:--r- I II 0

30• ....:~~1 3)g' e ,. 0"" i '" I

13231. 13111'115171:6

1'-_ -'_ I"-_--....!-I - I

i---JI

:E:rII

TOP VIEW

\ l:--...,........I ~ I T.t:i.. I:tJXEER CF GAUGE C; CUT3IDE stBFAG

o ~ _~ ~ I-"e:-.= 90~. (:cO:) l:LnIUR OF G.;t;GE c:; n;SII:E SUP.F.;CE312

1~-i JIJ,

~R.R. SIDE VIE..I

I L---I!-L/2-; II

' !-n( ~ II:;-- ----rr .... 1. - : I~ i I le= 1:·)0

( 3141 I ~---3-(;?)'~---"":i;;"-'--

, I I I\ ; I'\ I : I

1 - --........

'---J......!..'.... II '

--~ITo~a1

??.:':'a:1c::?rE';;~';:e

~e:e:'ence

s. Left SHE !Tozzle ar:d S~~ol:d

Figure 4. Contin~ed.

109

4 TctaiI Radiationi GT?

t. Left SRB Skirt Cu_ain

_igure 4. Concluded.

ii0

DUMP TANK8' DIA., 36' LONG

I--'I--'p-,

"_. • DIAPHRAGM CONTOUREDSTATION NOZZLE

SUPPLY TUBESUPPLYTUBE THRUST ABSORBING 42" DIA., 60" LONG i(/"IEATERS AND STRUCTUREINSULATION :NOT SHOWN)

Figure 5. Short-duratlon Ludwiez Tube Wind T1mnel.

OFSTl::.~

So-J/tc:~' Fu;)....J

CUp.jl.~k a,o\SII,,)TiZ1l..FI><.~ _.6----v.

STWl~~)-

,NC. 'D'~l2: of F~KJ

.----r.37i~K.~LUAJ \.<.J A:.J~01--1 "7"72S.T S~<:"T'''..J

/Dfii"5TIl. tJ c..T u:nJ 0':= 5,IfA,,"l:::1i \\.-rC~T S~Ti<TI-J <::<:lI...}DI-no,u~

-,C/Z ;--t /.-.JAT' [>.tj

/

-rUOlJCL

------_..--

~

1!'OJ

clrF

........--+--+-11-+-+1-

'>..lC.'PlC:~T C.I<:)JT~

E::><PAuS, Okj W~ve

Figure (). v!r,ve di:Jcrnm for 'l'IJbc' \I:i m1 'l'llflD:~ 1.

l.

•LEADING EDGE OF NOZZLELIP EXPANSION FAN

EXIT PLANE OFNOZZLE (Z 5' DIA.1

PRESENT TEST RHOMBUS(SHORTENED MACH 4.5 NOZZLE)

fABRICATED 4'(APPROX)--- NOZZLE LENGTH ----,--.........f------~----.:----_~

____ DESIGN FULL EXPANSION ..-.I

NOZZLE LENGTH

Figure 7. Ludwieg Tube Free Jet Test Rhombus for MA.CH l~. 5 nozzle.

ORIGINAL TEST RHOMBUS(FULL LENGTH NOZZLE)

-

@

a. First Stage Configuration: Front View8. Model 19-0TS installation in the Ludwieg 8Figure

Tube Wind Tunnel.

114

@

b. First Stage Configuration: Rear View

Q Figure 8. Continued.

115

@

c. Second Stage Configuration: Front ViewFigure 8. Continued.

W

116

d. Second Stage Configuration: Rear ViewFigure 8. Concluded.

117

100 msec

J-lJ-l(Xl

T4, A/V.~~ CLOSING

r----------:-- 100 mBec--------...~-

I I~-- FLOW BREAKDOWNI STEADY Po __ ., - -------:.------------+

III

!~-,_SRB_ Ig~~~ . _1f_-_t_--'

J'3L A/V OPEN 1----------.....'-..

. .......... ,

l\~ '~'"AUTOVALVE (A/y) POSITION TRACE I -".=-====-..-\.:.:~.~~==c.....=.:==_+_-----___.,,(

a. Model.Figure 9. Typical operating data.

•

100 msee

i

/ \,

Po / o - total conditions

Pexl IL/ ex = Ludwleg tube nozzleexit plane (internal)

SW = Ludwieg tube nozzlei' exitplane(external)

Pex2

Psw2 _ FLOW '.BI_tKDOWN

b. Tunnel

Figure 9. Concluded.

_ B & H TAPERCDRCALSPAN CALSPAN VIDAR 6 VCO'S/TRK (MLPX)

SIG.C0ND. AMPLIFIERS vco(66) RECORDAMPS.MODEL

i

lI

GAINS I

o_To1oo L__ _

EVEn_((CH) .-,IRIGTEE(CH13) .-o'om_DR(C_I_) --'

iv & o.ivPC ISIGNAL TO CALIBRATE VOUTPUT DEFLECTION

5HROUGH _IE Q-METER

o

CEC O'GRAPH CALSPAN VIDAR B & H TAPERCDR(_O"/SEC) "Q"METERCCT(_) DISCR(12) R_ROD AMPS.

(12) 2 _mc/rAssGAINS SET FOR (12 _I)

0'GI111_DRIVE (CHIb) ..... '• I

Figure i0. Vidar data acquisition and playback.

Yo = 0Z_:4EI'CSITION;_i.

O _IIIN-FII/4GAUGE RAYALONG NOZZLE CONTOUR

0

s_EPo_iI_oN/i2 ss_,_PosI_oN#3i NOZZLE: //2S_4E

llO

0 = 2kO°,2700•3000106-109

I lO2-1o5 !

(\.\

"_. .

NOZZLE: #i ShalE NOZZLE: NON [NSTRUMENTED

0 = 95°, 125°, 155°, 185°

a. W_thoutGas TemperatureProbesFigure ii. _,_I_,nozzle orientation.

Yo =0

SS_ POSITION /11

O _[IN-FIII4 GAUGE RAYALONG NOZZLE CONTOUR

8

Is_>meos TIoN/t2 166- /t3

SSME POSITION

I

NOZZLE: IIATBAND

50 0 = 255°, 270°50

.lO 119

lo6-1o9 115-118

.114

NOZZLE: //iSSME NOZZLE: //2SSME

0 = 210°, 240°, 270°, 300° 0 = 210°, 21_0°, 270°

b. ;lith Gas Temperature Probes

l;_ure ii. Concluded.

$Ot_RCEDATA P_E?_CE$

A-1

D_7 .....SOU..... DATA R_,'=._,,[CES

DATA RCCkZTELLi_P/LATI0NALSTSAEROSCIENCESD_AR,_,_hT

Wind Tunnel Operations Aeroheating GroupGrouo

Tabulated

(R. S. Crowder, Supervisor) (M. H. Harthun, Supervisor)

.,_.dTunne! Operations A_.o_.e__in_C-rou_Grouo

Osc!!1"_o6r_on_-_'I

(R. S Crowder, Supervisor) (M. H. "-"- _,_ Suoer-_-isor)

A-2

A_oP_IX B

GAS RECOVERY __,_E_?URE DATA

B-I

Table BI. IH75 Data Gas RecoveryTemperature(°K)LiteralData

riD - No Data DNC- Did rlot ConverqeAI t. Run Fos Pos Pos Pos Pos Pos

__. _#;. Pos Con_ments_ 752/155 753/I 46 754/I 48 756/234 757/235 758/236 759I

i 130 ] 39 D"C 293| 2890 ND ND r,D ND . ___

_140 ] 40 1544 2180 3016 ND ND ND ND I150 41 I 1302 1371 3419 lid ND ND ND 2'nd Stage Config., 1

42 I 1384 1192 2223 ND riD ND ND !

170 43 1137 917 2027 ND ND ND _D I--]L-f

140 45 51] 447 701 615 ND DNC 435 II'-O

100 46 808 829 842 863 816 948 ND

]20 47 646 684 625 1065 DNC 1373 ND__ L....

130 48____ 690 617 931 DNC 558 812 ND

140 49 453 635 818 624 529 ND r_D

130 50 744 639 1072 735 596 1071 34] Repeat of Run 48

.]20 51 711 876 1023 1371 987 1870 467

10___0 52 riD 882 rID 944 929 1068 583l

Table B2 Test I1175Heat Transfer Coeffici_ent (Cal/cm2-sec-°K)Literal Data

BD - BADDATA N.D- NODATA_

A1t. r<un Pos Pos Pos Pos Pos Pos Pos Comments

Eft. #: 75_2_/155 753/14_ 754/148 756/234:757/235 758/236 759 -_---GTP/PRESS(POS!

130 39 1.53-03 6.97-0_ 4.21.03. PID f_D ND NO

140 40 4.30-03 6.32-0":' 1.63-02 HD 1.1D liD ND

I150 41 2.18-03 6.09-0". 1.06-02 riD fib lid ND 2nd Stage Confiq.

160 42 8.98-04 5.12-0Z: 9.17-03 ND ND ND ND

170 43 1.43-03 6. 09-0_ 9. 23-03 ND 1.'ID ND 1'19!

140 44 2.41-03 1.14-02 7.53-03 PID liD riD ND

140 45 1.67-02 1.76-02 1.59-02 2.37-02 rID ND _.09-02

I00 46 4.74-02 1.66-0:1.02-02 8.58-02 4.40-02 2.09-02 PIDI i ,

120 47 5.42-02 I.-_5-0_ 1.71-02 1.66-02 ND 6.36-03 ND

130 48 9.61-03 2.38-0_ 8.55-03 BD 6.02-02 7.23-03 ND

140 49 2.26-02 1.12-0_ 6.63-032.52-02 6.75-02 riD riD

130 50 7.69-03 1.94-0; 9.67-03 2.46-021 2.00-01 3.62-03 4.43-03 Repeat of Run 48

120 51 2.72-01 1.15-0; 4.99-03 2.68-02 1.3_-QI 1.20-021 7.54-03

100 52 ND 4.62-0; ND 7.67-02 7.34-Q1 2.79-02 1.07-01

Table B3 1"I/'(5Data Gas Recovery Temperature (oK)(Input Data +2)

rID - No Data DtlC - Did Not Converge

Alt. '" Run Fos Pos Pos Pos Pos Pos Pos Com.m,ents

Kft._] tf"- 752/155 753/146 754/148 756/234 75_235 758/236 759|

130 I 39 1369 I093 I081 ND ND ND NDi

140 I 40 831 967 I091 ND ND ND ND

150 I 41 759 772. I148 ND riD f_D ND 2nd Staqe Confiq.I

_160 I 42 740 713 970 ND ND liD ND!

170 J 43 687 603 931 ND {ID ND NDi140 J 44 791 597 850 l'ID I'ID ND ND

I

140145 421 368 500 431 ND DNC 353I

I00 146 560 J 565 556 549 581 593 ND _120 47 484 485 448 648 DNC 752 rid

130 48 476 450 605 DNC 432 525 _ID...... I

140 49 DNC 320 472 riD 521 ND ND I

130_ 50 499 469 672 507 454 701 303 ___ R_peat of Run 48_'

_ 120 51 494 587 670 755 633 89_ ....3__.___

! '1O0 52 lID 590 ND 607 DNC 657 434 1

.... i

............................ I _] _I

) ) )

Table 19_.Test IH75 Heat TransferCoefficient(Cal/cm2-sec-°K)(InputData+ 2)

BD - BADDATA DNC- Did Not Converge NO- NODATA....... ,, , , ,

A1t. Rut, f_cs Pos Pos Pos Pos Pos Pos Corr_.ents

Kft _ 752/155 753/146 754/14_ 756/234 757/235 758/236 759 --._--GTP/PRESS(POS)

__]2ZL_.__35 2.-29-03 7.81-03 14.81-03 rID ND ND riD

140 __40 4.55-03 5.91-03 1.89-02 ND riD _ND FID

150____412.33-03 16.43-03 1.22-02 rid ND ND ;dD 2nd Stage Config.]- L

_._]_6g______421.14-03 15.41-63 1.01-02 ND ND ND ND

170 43 1.70-03 6.31-03 1.02-02 tdD ND lID ND/

140 44 2.r.'4-03 1.16-02 8.19-03 ND riD FID NDIk,n

I___!__Q__45 1.26-02 .02-01 1.62-02 !1.12-01 tdD ND 1.10-02l

__!I_)0 __6___ 3.96-02 II.54-02 1.06-02 8.32-01 3.06-02 2.84-02 NDI

__]2O____Z 3.37-02 ji.57-02 2.41-02 2.25-02 ND 7.88-03 NDI

130 4P_ 1.32-02. 12'47-028"95-03 BD 8.31-0_ 1.11-02 ND

140 49 DtIC 1.47-02!1.41-03 ND 2.31-02 rID ND

130 5_ 1.14-02 1.89-02i9.89-03 3.84-02 3.76-0! 3.19-03 4.52-0J Repeat of Run 48 -I

120 51 7.88-01 1.18-02 4.82-03 3.67-02 2.28-01 1.32-02 6.85-02

I00 52 ND 4.49-02 riD 1.25-01 DIdC 3.10-02! 1.03-01

UIA[

At [

SISrANC•I

oH

"SI

- f- - f- =1=l--l-}-4---I--1-- ~~=t--f- - - ~~ _--+--t-+-....--+--t-+--i--+--t-.J-+-~-~

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1900 . 464748

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-..ClI~I--·.r ~~~ ... l. :·l~~~l~:--r-~ ·-~~f~!"J~:L·~I,::·;~' ~.700 ;. .:! !_i' \ ·O·_i_._-:-L. '~"'-cL.~d~.±~_ .. :·::···l·~~--J' .....J..u J.L,Lj:·lu)li;i"-I··-f!~+L_1 .' •.

. : I : i . ! : Lj : ~j~ :!.:::-.:. ~r·f-r~\:.:;.·:·.:> :::.;:::::'::,-"·· __··· ..··_··r .. · I·.. ··· ..-,···1· ..·· .. I. .. I, j· ..·---I·····::.. L::· ..500 : I:: , . :_.~: . i_ ~'-j" .~~_<}_~ __.>I,! .: '.':: ! .::.:'::1 ': .

• : .1.: I I. ~~;:.. :. if : : I: 'i"'1 :j·,I·:.::l.,;:!·I.. :j:·:I .. ··.__.__J. .!._.l. l. .. 1· I...... '1 o· .. ; : .~. '1' .. ' .. I .. ·· ·····~······' I· ..·l

~.! :n-;-J-'-, '. ;'7r I... ; :~..+..l~l·:;::· .:.:;'.::I--;.:::i::~--.:300--··1-··~· l _.- I .. \ .-:.:. ··- ......1..··:- T-·:·· j·: ! ':'''j .. :::· .. I· ..·::·!,· ;::~!-;:-:-I-" .

100 110 120 130 140 150 160 170

ALTITUDE (KFT)

Fi5ttre:35 r:;est I:-i75 Ga.s RecQver'J Ternperat1J.!:e ~·:eas~.:.re:~_~:'.ts

on 19-01'8 Space S:'lutt1e Hodel at Position 752

B-10

POS 753Run39

3000 4041424344

2500 454647484950

2000 . 5152

A 8 : : ... '1 ... ; ! . i :'!I : I 'I .,' .. :.. ilo d I : I . i: i!

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'J "1': .. : .. _L.~.L._I 1 ... :.... 1..:. I ,1 ... : ...1.: .. : ..,=C.. l:• • I· : ! : i: ~.' i U ---: .... , ••• : !

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-;;- Literal Data ':"11

• i . 'jl. : ! .1....:.. L... : .... i ... I...~ B. - Reduction Based on: : i' : I : I : I : ! ; I I

:: 1500 .: _~.a1 Data t 2 ~r~:~.T-:..l-..-; .:....1 .. :..1. .. :.. !I': .l .... ~,c:: .. ' 1 • I ' i . I . I . I ., I , I I' .,~ .~l: I ' ,: :.. L..._:_._J _1: . ' . _l-i_l __._!-.....

~ ; I·: ·1 .. ' : .., :.. ! I : . I : ~ : I : !;·I . I~ 1300 ::.: '!: \ . ! : I :! :: !~ -.,. J' . i II: II -;---.;---.--.--1---

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8 1100 .. -. .. I. d- . . :..-.... -.--... -- ._._._. ~_~_ .. -O.. -- .

LJ,.J iii I. i : : . , I' I I :c:: .. 1'-' .\ .. j ... ;. i . : . ~ . ; ! . . .:! .V'l .: I ~_;_•• _._... ! - ~__J-_:. __._: j __ .... ~..~ l I ! j : I; Gf I I I ;1:

900... '1---;' \,.. , .... ";'j'" 1 __I -.0 I .. i .I; I;

I . , .:' . 'I' I:.,. 1,-.;.. 1, \-- q-~- ., .: . I 'I::.. I : .. ..;.,I:: , ~I I~

~r:...··!l ..:--·j--~·~--!I .. +_· . '-:'~I .. ;.!.: ,_.l, .:..5'11,,, ;.: ....Li ...'. '.! ..... \ ""-"

700 ';-T I--~--:-i-:_L-~._~~-_'-'.' . 1 ; ,--:,¥-.._.-:--'-r'------·~ ....j':+"r..:---j'-~·'1"·±8:· 'j' . ~ "," j -i-+-t·;-·:....l·;.. -j-. . ! . I

. I: I : rr'±j" ·'-'·--I-..,.--q":-'--"T --1'-;....--·~.-\l-" ...

500·f : 1.... ~ ....I·~ ..1"j"." T·1...... ·:· ! :',: ! .: .j... ·"l·.· J' .. \·,1· i·I·· \~ . _-4__ I ~- . • -.-+--.-.--,--'.';' -f·: ,,1---; L';'j ...+--j -, ~ --- i _. ~ J_! -:-t++~ --H"'i'~'i .... !-'-,.. . : h : I . i : ._-~--:~: : r-' I

300'; ... /....1.. --/-...:....1.; .. I"'-:--j ..:. 1··;..·1· . ~ .j . ~.. ...] !...j. ... : I.. ·100 110 120 130 140 150 160 170

AL TITUDE (KFT)

Figure B6 Test I:-I75 Gas Recovery 'I'e::rgerature '·leasure:::er.~s

OZl 19-CTS Space Shuttle '·:odel at Posi~ion 753

B-ll

3500 i

IRun A B A - Reduction Based on i ! . i POS754_39 0 _ Literal Data .... I .....

40 m c:rB - Reduction Based on ! I ' @ i ! I :41 0 <_ Literal Data- 2 I ..... i-I.--: ............ _

3000-42 _ i i / .i-I i 0 i -1 _ i , _

45 o .: ..!.....2500-46 d • . i ; . i ;__._i.___"......." ! _' .:. , _.. .:. . .it _....

I _........

__84950°°° ___.':I,_.i-...':_i._._L:. I_,,__-__. ._i."_,IL-- 7 i-: _': ,"2000 _ 51 _ .....

: , -I ..... ]-i ........ I'_ _: i ........ : : : i... ;:- :--!.-].....

.i....::.... "..... •...... ' := i ....... " t : "I--- ! . , .

;5 ' I I i , i I _ IIll I " I - -- _ - ; .... i_- 1300 ......... i........................... L"' I_- ...... ! z '. ! I l i . .. : i ]I

...... .j..... i z

> .Io ....... :I ........ ,..... _ " _ ¢r ... '.... •"' llOO _ _ ........e_- : ]

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...... i t : "'_" '...... ! .... ,! .....{ _ "....., .... •

' . _.I...._......._.._. .I. ' I i . i i:i-:_..... I : : ;....... _-I-! I ......_--,........_--_........700 ' _, I : : :

.........i, ....± :...... _. ] _ , _-!............ '........ ; .............. i .... """ :

500

:'_!!' __ l I ....':--_---::.....,-_-i-' i I ' i .... i300I00 II0 120 130 140 150 160 170

ALTITUDE(KFT)

Figure B7 m_st !_175 Gas Recover_j m: ,_'_.',_ _ _s ......_-.... L_.p.....,u.-e .',.e_'i........._

on !9-0T$ _pace Shuttle ilodel at Position 75£

B-12

.--- 2300 _Run A B A - Reduction Based on , POS75639 0 (5. LiteralData , :40 n Cf B - Reduction Based on t ij :.41 <> _ LiteralData .+2 :......i_:_l"i::i......

210G 42 _J q" , -_--.._.._- '43 U _" ] I '44 0 Cf , ii ' I I _i_:z;-I:_

45 ,c,_ I iL: " ! I ,..:.._._:!1900 47 zl z_ : i [ i ; i--. -i. ! { I

.-.I...: ....1.... : ...... J . J "i:"t'-::ih':t:'-'! ......48 _ _'__L.._I _ ! :: i _ i : '49 u d ............... :...t. :1_:.!i i : I

I I.i.ii::i::.: .t17oo51 _ < , -.+:::t : !. ! : " ,:.

,+ .....t;4-+::+....:......,:+...._.... i'_....i4t:+i:_ ::!I:: 't: ' ' ' i i+!l::-i:....."/ 1500 ........ ! ....... !........ i I:' :[ J : x[.... :.:':': .::: ! . :.: . :

"' ............... i+ ....+I+'.................. • .. , +........ i .. . , . :

I-- I _ 1 ......€_ : ...... +--"_ , q ' i I I i

,,"' i • ,i : ; • ' _I :+] -! ....i+_- 1300 ............. J ...[...... I.... 1, .',' i ! II-- .. ": .... : ...: ...... : , :.. i

I ............... :>" _ i i,,, K ............. !...... . ..... ---T-'."P--_.........

> .... : i [ '+....... i : ....i--_- 0 _ { '" , .......

U i _ : "

"' llO0 • T...... t_ I --< , , I t I '!

7 ............... : ................. "................ i...............7........t

i : i i, !.......... t ...... :.. . ! l ..... :..........I

900 : ,----_ ....

+ r, I , !_1• ' : I : _ i "/ I J '

z I t• _ . i .i , : I : O I • ' _ " i I........+:T "

700 + -- "-T: ......:....i.........? ---: -_• I : ::::/ ;/ ; _. : . ! 1 : ;:.:il:_;:l ....:...... :................. ;......--J .... -_ .... i ........ i.... I ..... _.. • '.__.

I i j I:I,. i+ . i;..,.. I•:!.-', • I : ............ : : .... +::-_:+-:-I.-.-:., , , . . i • .. '500! - .-I...............0 ...................I......__....L_:__ ..::t_:: J• l ; ; , / . • .

• ,. .;..... •..... ! , . ._ : I

I !T_T I ' ' ::.i_::ii+.......... , ..... :......11 ' " ' ......i !......300 ' . . t :

O0 1I0 120 130 14o 150 160 17o

ALTITUDE(KFT)

Figure B8 Test _-H75 _°_ -.....___ Recovery Tempe_=+,,r_ ",; _--",,_ _,__"-;-on Ig-OTS Space Shuttle l.:,odela_ Position 736

B-Z3

2300

Run A B A - Reduction Based on : : i .I ....i I !.39 0 C_. Literal Data i i ; ; .... POS757

-E I!i _ _i --40 c _. B - Reduction Based on ' ....i " I i . il41 0 0 Literal Data - 2 ' .......... ; f : i2100 42 q " _ ' ---

! T .,I i _ _ ' ' i44o _r- _.... il..... i. I ..( i ......i.... i (1900 46 0 d . ! i:i "

i..q .....47 z_ _IT ... ,. . !i - . I .i ......i. "I : I _ I : l ," - .... I '_ ; ' " ' '

i .... "-T---' I ' tl i I •49 = u" i i::. :;:L i ' ; i" -: .... i50 _ _ ........._--:_:-':............ I.: i i ( I! i1700 51 _ _i__ ;{;:;:1 f ' = ! [ !: ............

.........:-= =--'--....._ !: ....... i" ....!-1- !=" _ ......... , i ' i.... !T-T] -_- -T-I_ 1_oo...........! i _.......i:.................i :I ...... :!1 "_......! . (:......-_:_ -! ................ :: i _......!..........i ( i .... '; i::i .t :i :i...... i............... i :

= 'i i 'tii ' ] '[ : ....:'--- i .......i........i.......i- ........ : i ........... _....1....i..... _ ,1300 ,- ' ' l '.

- i i,: ........._..1._.,.,,I ' ' _, '.... _ ' I .

__ i; i I !ii 1!, _- 1 i I i ':) 'I

- , , ,i_-_i l_- ! ' _ _ •

,. I , •

................T',: ': _ _1 _ , ,I -t _- ..... ;-4,;_....... : 11 _:70O

.....,'I..,_-,,_1'..........' t i/:-;,-_-!',-, '...... :1 ,, ' ! : , ' : " I.............._ I ''_: _ i _ ! ;_' ' il:[ :i? _--:....... :........ ;--- _ .--£ 0 i...,..:

._--L:L...L..I..__..__ .... i- " : ....! ,. 1 : I ;

2SO , _ . , ,I@0 110 120 130 140 150 160 170

ALTITUDE (KFT)

Figure B9 Test z-H.75Gas Reccve_" m.......,_: ", o _-on 19-OTS Snace Shuttle Model a< _ "_. osm_..on 757 __.

B-14

2300Run A B A - Reductie.-. -_=sedon ; • . POS758I

39 0 (5 Literal _.:_ta .___ : ,40 _ CrB - Reduc_io.-.S.=sedon ........41 0 0 Liter_l2.:-_- 2 : "_:J .....• i _ I

2100 42 _ _"...._ ; E ]

43 _ _/' ; : ! { " " :i ...... : '44 0 cr , ,: : : -!_ i45 ¢ <_ : i i , i._ '

46 _ d ............: _'.....: " • z:: " -I:-!T _!

50 _ ,_. _........... i _i...:: I : I .: i :1..;::.:t. _........... : i "':'"t ...... :!:i'"/:':': • i i"

170C 51 '_ _'. : !- - ! • _ ,. i:.i,.:: i.i-: :

s2 v' ; •.: ........ ! L.... --:-"F/I! :-:] ! ...... ;........ ! . ;. : ..""

"-I " t .............................. i ........ :..: .......v " _ - i, ......

,,, 1500 I , : I i!:II--- I i ; ' • : • • I.. !....._-- _.,,___:.... !

,'_ , : I : _'F'---; ......i 't.IJ • --- - - " ...... '.. , :...!..:. . . I

,,, 1300 ......................i ' I ....': :'I

>. ,

f- I._ i ; ! [ '> I....... i0 "1 .......... : " " " : - " ; I ......U ' ] ' I : :'" II00---- .............................................

] : ' ' ' : '. "i_._ ..... : ............................... _.................................... _...........

: i i ; _i I i9O0 , .... _- '-- i- ...... i..... !...... !.......... _._J

..! .. -- --_ ..... ! i i { ":............I : t . . : . .1 . -I ": " _ :

i

500 _ i : _" ' : :

1 .. ; t I .:.... !..... _ ........ . , -: • . .: : .........I........... _...... _.... ............................... J

: : ' ................ I.... i .! ....l.. i .... i...._......300 I ' ' '

I00 II0 120 130 140 150 160 170

ALTITUDE(KFT)

Fi@ure BIO Test Z475 05s = .... '• .eco.,e_a Temperature_.[e_sure_en_son 19-OTSSp&ce _,.u_ i,[cdei&t ?osition7_

B-15

2300Run A B A - Reduction Based on i i ;_ P0S 75939 O d. Literal Data , i _ , :40 m d B Reduction Based on _. 1 ! ! : I

.... i..... i "'" i"

41 <> <$ LiteralData ._2 ! I ......! _ ;

43440_' '::/_'" :'!"I i l i--...... i t' _ ,I "'l .................i i i

°<' i-!-i-'! -.:t.! '!49 i_ i_' " ' --_ . .. , • _ I

° ' +....!......................1.......+s_ _ <1_ {.,;li ! _. .. : ..... i_7ocs2 _ ,'. i _-.!i i liI_i+ ' 'i i

i •_'_i I-! .....:T-I....!I! I: .....: I I _ i

-+-! ! , _ : / 7!_t:! 1 !: ] ! i 1 ; ! .....,, ii ......

{ i.... • ,....!!tiilt -T:iN 150C _ -'" i i--_ ........ °.............. ; ....I--

' II +i;l I_' r _ i• _ii ! ....',, I ! "TT..... ?............ !" . ii ": ii ': I I l !"' 130 ! , . i i i i ,"- I i :.-i....t--:--i-._--!.-..i.. t _. • : _ "i : •> I i i i I " I : !o ............. ) .... I----:'--#-:-i-+-i ---i-_--t...... !..... ,, ..+ I.. i " ' • i • -+ '-",,, , ! I : ! , ! _ , ' : . :

-_ "--'-t-- "---1---- -- .... L .... -- ............. f .................llOC i ' : i ' • I . , + i '

< _ l :_. !+.I. L I, l: I _ ! :_ i i_,_+ i _i i.

900 . 7---i-t . :- -,T--i'----l:-7--1---77--i : i ! ' -; ..... : I '71 '7!:7 ....::1-:1: r ; 1:_ t _:.....: i !_ :_ !: _+_. ' ' --...L.----:-- , i , ; , , , " --_ ' ' --I--- ' ' -- ...... :-.--L.-4=----___" . __

'i I '"++ + '.................. i .......... :..... : ........... .-:: ............... i.-.: ...................... .' ..... :+.• , i ! : : i ' : { : ' t ' ! '

! I ] ! ! _ ! : ! ' i / : I l ' + , ]

70C ..... :.... F-_-['--I-:-T]--T-i, . i ! i!l ...., !--T- '-',.......... l ............................ I .............. 1..+:... I ......

': "I ..... '.... " _ T"t': "'I....i....t:": --.!+.-t.--i ......... i i............• i + t ', I +._.1:.I ! ! : I ! I _ _ , I _ I .

50C ..... _----_'-- '.- "-r------. .... , : .... + "- "-: - 1""_-'i'- -- _'-'+-,,, ..'<...i....! '..! .. ,_..i....1.__...._....!...l_.::..i...i.._!.....,....t..; ......... ... i .-._+,,,' I : i + + !.l t ' I i:1 . _ ! t i ! _ i ; i ' t _ t--_--:---_r ! i + i i_i.., i,.i i ; 1 i--:----+---T--I---T--...... : _ : I + I-._....I....+_, +.-_+-.'_.-,.---t:_ I i +I : I.-:--.i.._. ! -.

300 I : I ' I + ! I ' I - I : I ! l ,

O0 110 ]20 130 140 150 160 170

ALTITUDE (NET)

+m_Z--u-_eBl! Test _7%175Gas Recover/ Temperature _-_+...........ourem ...._+son 19-OTS Space _nu,+_l_ i.[cde!at Position 759

B-16

lO° .POS752_I_:--_ ...... ' .............. ,-P,un A B POS 753_39 0 (3 _ A - ReducedBased on

, -41 0 0 -

............. : --42 _J _I' 2 _. B - ReducedBased on; .... !---" 43 _/ _ i _: :.: i . - LiteralData-2i _ j, : ' -44 0 o" , ......::!-: --

-': . : • !!:.l:i Iv : :- : ::. : -46 0 d" : ...... I ,. ;o .. -: ............ i .... :: . 1 . . ., 47 z_ z_ ' ... I...............

...............I iU , . . L '

............. 48 m _" ......... : I

, 10-l " 1__49 '_ _" ' <F---.I I I i )E i L 50 _ _ i ( (IJ --- I i 51 'q _" ' i

- I I L-52 _ _ : _ :i

° ' _--_' I _ ! _,_i_ ' :"-" i ---I 4 l4-J i

' _ " I_ _"_ , i _!-. I ..... --- , : - _ ...... : ...... L........°r'- ..... ).........

• I : ! i4- : : I_ t

o -. ..... . i _ .... _-- , ;-= I -o, ' .... I, '- .... • "o'. I : LY!!!:! !-!- i_o ..... I 0' , " i

4- 10-2

_" I _ i __-_1.-- i I- ,_- i ----'+ i : " I _._J _ . : I .

..... .......'.....'.......:( io .._ .... i ............... _..... _. I I -! ..........

"_ -T--: "--: ...... i .... ': .,.i ....u i ' " "

o . ...._ ............... ' .... _ ..........................u ', _3 ' •

..... _ _ ...... l10-_ ................

I i .... ,---- ,a ! I ii ( I -] ..... ----_ i_............ : I T--" " "-/: _ ( i .

O0 120 140 160 t80 O0 120 140 160 180

ALTITUDE(KFT)

l,'.i,,/_Iz'e }_i_. '£est I}175 bonvect._.ve ](eat Tz'ans£er (_,oef'£icie_t I_lea_uremeni;'.; on 19-O'i'_ _pace Si_z_CIo Model.

10oRun A B :Y--POS 756 .._ _-_POS 754 - _ ' - 39 0 Cl I! A - ReducedBasedon

: ' :_ _ 40 n d ...."i i '_ i -. LiteralData• j

! -i: :: -434241<>£/_jd_,_ -_!-_-.'---TT-i_---T--_- LiteralData"2

on

.-TT-_.I

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.... ; ..... i , ..... I, i ...... , 48 o _ ._ ..........10-I : " : ' _ 49 m d I........ I <F" , • • ;u ' '. i I I" i ' - 50 0 _" "='

-_ 1 7 I i I i i< i - 51 _ _" ! ! i :.__ ' _ !: I i<_ : ': - 52 9 v" : : _. i:•J ! i I ; • r i i

j l.--_--_-...... I L............. -- ..... _ ..... .k---- .............. ,_.... _.... _........ i.......

• . ' : . i . • "--?--'- [ .....! _ _ i ! ' " i '°r- i : ; • "

. , ...... _- _ .0 • ',

i ._ :.-. _ : ; " : .,_i::-i:..: l• _ • . • I .... I

. J " 1- " ; _ T..i._/) :T " . ' •_ --:-! ! _ ! _ .....

,o ....F-_ .,T..... i ; . ;oo_ I _ _ i' i

'-' i u ! i !,. ! I i"T"

....:..... ...... _, " I : . -- i....... I ...... '_'........... , T.....

I i . : i . : .

u " :').... i' : ........-.....i;......;........ i_.....-_ __T-----,__i-=--_-' ...._......_L____ .....____-=-.................:i....-....... -.............- _i........'_'. i.......:> : . . : : ( ; . : : . Jo ! : : ! ' '

: I . _ ' , " " '. " i '

.........._ .:: ) i: f ! i ..... ::?_.............._ • l:............I0 ]- _ ;: I

' 1 "! ; i : : ( . .I ...... I ' J-

+__ . j ) , :

O0 120 140 160 180 00 120 140 160 180

ALTITUDE(KFT)Figure BI3 Te'_t I}17_ Convect:ive Heat Transfer Measurements on 19-OT_!', Space Shuttle Model

1 ) ,

0

- " ' ' '- _ Run A 13 --POS 75(S._-__1.... A - ReducedBased on

_- ' -1-------!-_T-;_!_39 o o -- tLiteralData

• 40 _ U I -i......_.......I 41 0 0 .... i .; -.___T.-.--B - ReducedBasedon

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.-. - 44 o o" . -I-;- . "o . 45 0 0 .....

u : i 46 I3' d .. I ........ ::I ................................. 47 a ,_ ........ , .. T-.----r-....:-:-'-T............,-,,,' '. _ 48 o _ i ....... . , ( ,

E | I .... ' " '

u 10- i 49 a a' ' I ;

_" l 50 _ €' _ -......1 _ I . ' .

-_ " " ' i " : " " i' I

_- • • T ' ' 1 ..........!....... : .............._. ..... -T------r ....................................... '......... _ 'i

"" :3"-.... '-......... ' ....... r". i t ::"- '_ ' _ _.. ; .IT ' -- : I"-_ "' ........ i....... _/"............ I : '. 'o , ]

= _ i i . , ,I ( * $ * _ I _ l

F- ag " T

= I ;....... _ .... : ..... :--( .......... ',..... ! ..... i ................... ": ..... i"................. ' - " ' I

(" _ - : . : . . :

o . " i :" ' : I "

t ,__I t i-- ) i 1 :-- i

I 4........... +.............i i

00 120 140 160 180 lO0 120 140 160 180

#.LTITUDE(KFT)

]?ii_ure]311_Test ]]I'(_Conveetivelleo,t Transfer ;oe£1"LeJent l,.leasuz'em,_ntson.I()-OT::3f;pa_ce:_huttlel_!o(le],

I00 ! _ 4--Run A BPOS 759 A - Reduced Based on .{__39 0 (5_I Literal Data: 4--40 [] E/

_, : [_ I 41 o _5_ i_ _:: i_ B- Reduced Based on ]-_42 _J _fLiteral Data -2

i i43 U ry

.......... 1 iiii_i I _ 44 0 cr-_ ..... :45 0' 46 0 dU : [

: 47 a -_

_' ........... j ; 48 _'=:u 10-1 ._ ........ i 49 _f--

' i • i 50 e ,_u I r--

-: 1 i_:- l _ i

° J:' I ;¢# . _ . -r...... T-..... _ ...... ; .....

u ..... : ...... T,m.---_ "7.

f"" ! ..... Iq..,tf)

,u 10-2

° i I I,.,f.. : : : - . .

> :" "i. : i i!i:! ::; : " • :ou i :

" ; T? I ...... Ira---T-: --?- _ ; , - "

" - .I !1 !

-_, I i

100 120 140 160 180

ALTITUDE (KFT)

Figure 3!5 Test IH7_ Convective Heat m_fer ,'_ =':"4 _....... _ez_lc.e.._Measurements on 19-OTS Space 3huctle Mode!

B-20

APP__--ND!XC

_w_.iDATA T_E CORRECTiC_'T

C-I

F:,I TAPE DATA CORR.ECTIO,X

The Rockwel!-supplied F._I-_lultip!exTape Recorder System :,as used to

record heat-transfer gauge and gas temperature probe data. The outputs of the

thin-fi!m heat =ransfer gauges (which are proportional to the surface temmera-

ture of the gauge) were recorded on the F._Itape. After a test :-an, the tame

was played back through an analog q-meter and the signals proportional to heat

transfer rate were recorded on an oscillograph. It ;,asnoted: that the heat

transfer data exhibited a droop that implied a severely !imi'ed 7C response

of ti_esystem. Only after a careful review of the entire data acquisition

system was it discovered that the cause of the droop _.;asnot in the cabling,

the mmplifiers or the F_I:,[ultimlexsystem, but rather in the circuitry power-

ing the heat transfer gauges being recorded on F;Itape.

The .oarticular bank of heat transfer ==au===.conditioning circuits

used with the F_I tape system were origina!ly intended for use ._ith :he Ludwieg _-_

• , ' _ _t OH-66 in th_ Caispan H}_er-tube tunnel However, they _e._ first used on _=-

sonic Shock Tunnel. The circuits have a ! pfd coupling capacitor in the ou_-

put and were intended to be used with the amplifiers having a l 5!egohm input

impedance. This would yield a time constant of i second, _hich ._ould have

been adequate. However, in order to meet the data acquisition requirements of

Test IH-75, a large number of mmplifiers were borrowed from the hFpersonic

shock tunnel. These amplifiers had an imput impedance of 190 Kohms and re-

sulted in a system time constant of 0.i0 seconds.

.in analysis of the circuit response for a constant heat transfer

rate has been made in order to determine the corrections to be applied to the

data. For a constant heating rate _, the thin film gauge surface temperature

is

Seymour, D.C., "!H-75 Shuttle Base Heating Test .Ina!?'sis," >USA _.ISFC._lemorandumED 33-78-16, _,la>"a, ,9,8. _-_

C-2

Analysis of the RC circuit to such an input was made using Laplace transforms.

The output (as recorded on FM tape) was found to be

2_ -Vz_ z _

where T = RC, the time constant, and e _ =_ zk is Dawson's

Integral and is tabulated, o

The correction factors for the recorded heat transfer rate were

found from the general relationship between _o and surface temperature To (t).

To<t) ToOt)- Lcx; d A

This integral relation has been evaluated numerically, using the technique

of Cook and Feiderman The relationship can be expressed as

-o I

=; itn -- "t; . ("_._- L'.ti a

Since qo represents the recorded heat transfer rate, whereas q is

the tr_,eheat transfer rate, the correction factor q/q° has been evaluated

for O -_t/_" -< 0.9 ( or 0 -__ _< 80 reset), the enclosed figures show To/T

and q/qo as functions of t/Z'. The curve for To/T compares very well with

that given by Seymour; however, the correction q/qo found here is signifi-

cantly different than obtained by Seymour using a linear approximation to

the To/T curve. Seymour's correction is also shown.

* Gautschi,N. "ErrorFunctionand FresnelIntegrals,"Chap. 7,Handbookof MathematicalFunctions,NBS Appl. Math SeriesSS, June 196_.

** Cock, W.J. and Felderman,E.J., "Reductionof Data fromThin-Fi!mHeat-TransferGages: A ConciseNumericalTechnique," AI.<%Journal Vol.€,

_ No. 3, pp. 361, 562,March 1966.

C-3

During Test IH-75, the Calspan m_plifiers were used with Channels 1

thru 41 for the FM-_itiplex Tape Recorder System. Incor amplifiers having

a_input impedance of I Megohm were used for Channels _2 thru 66. The latter

channels have a time constant of i sec. The heat transfer data correction

factors for each group of channels are listed in the following table, along

with the time during which the data were read on each run.

C-4

Heat Transfer Rate Correction Factors.

RUN TI_E CE_XNELS CH._XNELS

NO " (_ec) 1-41 _2-66

4 67 1.94 1.065 58 1.77 1.056 50 1.64 1.057 60 1.81 1.05

8 60 1.81 I.OS9 48 1.61 1.04

10 45 1.56 1.04Ii SO 1.64 . 1.0512 70 2.00 1.0613 60 1.81 1.0514 63 1.86 1.06iS 63 1.86 1.06

16 63 1.86 !.0617 59 1.79 1.05

18 68 1.96 1.06

19 66 1.92 1.0620 69 1.98 1.0621 67 1.94 1.0622 63 i 86 1.0623 63 1 86 1.0624 60 ! 81 I.OS25 38 1 77 1.0526 54 1 70 i os27 54 1 70 1 0528 66 1 92 1 06

29 70 2 00 1 06

30 70 2 O0 i 0631 75 2 i0 i 0732 71 2.02 1 0733 66 1.92 1 0634 66 1.92 ! 06

33 70 2.00 ! 0636 72 2.04 1.0737 70 2.00 1.0638 76 2.13 1.0739 76 2.13 1.0740 76 2.13 1.0741 73 2.06 1.0742 70 2.00 1.0643 70 2.00 1.0644 79 2.19 1.0745 66 1.92 1.0646 66 1.92 1.06

C-5

Cont'd. Heat TransferRateCorrectionFactors.

RUN TI_ C_NNELS CH._NXELSNO. (_ec) 1-41 42-66

q

47 64 1.88 1.0648 73 2.06 1.07

49 73 2.06 1.07S0 72 2.0_ 1.0751 $8 1.77 l.OS52 64 1.88 1,0653 52 1.67 • 1.0S

C-6

C-7I,a

.......-

--==

-;......-

-

tic::,4

~-I- --- '--

I-

= -

F= -+-=_ I~=

=

==;;:;:=

-

~

=

-;::=:=

-

-~

=-

t-- _

--

=f--

--

t: --i-;..;;..;..;...-

= ...;--=f- =_.--= -=

0=

f,4-

z

..


APPETDIX D

FLOH CALIBR4TION OF ~·tt"CH 3.5 FIBERGU.3S:NOZZLE III NASA/CALSPAH LWliIEG TUBE T"lE·JIEL

D-l

Su.r:unar.,r

A. series of calibration tests "re:-e :gerfor:::ed prior to Space ::,:n:.ttle

Test I:ri75 to deter:nine tne airflow char2.cteristics of the contoured !'fle.ch

3.5 fiberglass nozzle for the rffiSA/Calspan Ludw~eg Tube \iind Tunnel.

Su:gply tube operating co~ditions consisted of heated nitrogen (nosinally

300o?) at pressures (po) approximating tte :-ange req~ired du:-ing tte IE!S

test progr~~ of the 19-0TS Space Shu~~le sodel.

me average value of the Mach nwr.ber deter:nined ~ ........ ,...,~ -:he calibrs.ti on.:.. ......d.l..

tests is 3.454. 'Dlere 1.;a3 no discerniole ,,:rari2:~ion in l>'Iach nu.::lber ~1:' --cn

Rey~olds ~~~ber over the r~~ge of tte ~eS0S •

.L\"O"Oaratu5

.f!.. three-armed ral~e instr'..lI;len~ed wi t:l j?i-co,;-yress;;.re probes ~,ras ~sed

00 survey the flo'i. Figure Dl depicts the rd:e configuration ~~d defines

t::.e probe positions. 'I"ce £'10"-1 surveys ;Jere :::.ade ;Ii t:::. the probes loc3.ted

at the exit plene of the nozzle, at a lcc~tio~,~. '

..:..C: lrlC.:leS into r:czzle,

and 12 inct.es dmmstrea.'":l ':)f the nozzle exit. .in ?ddi tion, at tne nozzle

exit plane loca~ion, ~~e rake "ras rotated =900 from its nominal positio~

to check flow syrr~etrJ.

The pitot-pressure probes 1,ere inst~~ented ;rith Calspan PCB-37-2l

pressure transducers havir~ a nominal sensitivity of 1.5 v/psi and a

range of 0-3 psi. T-~e nozzle flow stagnation pressure was ~easured with

two probes instr'..lIr'.ented T1ritt PZT-37-23 tr3.nsdt:cers that have a no=.inal

sensitivity of 50 8y/:gsi ~~d a range 0-100 psi. All transd~cers were

D-2

FLOA C_.1.LI:DR:\TI01: C? ~'i"'..CE 3.5lIT IL;'SA/C..~LSPiuT LUD~,rIEG 'i'l)j3E

-r,---.,....." ...,7 4, "'~ ""\ ... r .......... .,.~l' .!..;:....:..:..'V ~"'"l.Ul:> 1. \..LLll..Jl:

calibr~~ed before and af~er nozzle flow c~li~ratior.s.

Calibration Tes~s

The nominal test conditions for t~e calibrations were c stagnation

~em'perature of 300°F and a nozzle exit stat-ic pressure ec;.ual to 1/2 t::e

ambient pressure at altitudes of 100, 110, 130 E.nd 140 KFT. Host of tr:e

calibration tes:.s ,·rere ::lade at "t.r-_e higcest s'1d lovest altitelde condi ticns

with only one run at eac~ of the two inte~ediate altitudes.

conditions for all runs are sun~arized In 1able Dr.

Tne calibration results for the lc,·;est altitude condition are SU''1."::2.-

rized in Fig'J.re D2, r,;:1ic~ shoils the r.s.dial districu:ion af -cot:: pi:c:.

:;;ressure nor::::w.lized 0] st2.gr.ation ?ressure s.r.d i,Iac:: nU::lber. Because no

flor,; asyrn..metry ,·;as detectable, the data fro.:: all t:lree arws of -::-,e 1':012:e

are plotted versus radial distance from the cent2rline. T~e identific2~ion

nu.zrlcers of tl:..e probes e..re s:"'.:.o"..;n along t~"'..e r2..dial dist3..:.'ice sC3.1e.

T:le calib~2..tions for :one ~~ig11est alt:' t~J.de 9.re sLt..7~arized in :3":'g:lre

D3. Tne presentation of the data is the s~e as lTI Fi6ure D2.

average Hach nunber of all the data shcvm i!1. Figure D3 is 3.493, -..i~:ere9.S

the average value for the data in Figure D2 is Because

difference is much less than the scatter of the data, a variatio~ ~it~l

altitude (or Reynolds nU.TIoer) can not oe d2tected. T~is is also evide~~

1::: Figures D4 through De. Figure D4 sho~:s d.s.ta~t eacn of the four tes-c

condi tions ~·ii th t:le r8.ke i!1. fixed. position. Figures D5 t11rou..g:~ De. co::-

pe~e datrl at the t~'iO extre!!le altitudes for varicus rake or::'e:ltatio:1s :=.nc.

D-3

FLC,T,,:CALISF'kTI0[_ OF" .... ._. - .... -r• ........ 7- -

i,.,c .......

_ne degreeof .f!o:,_"symmetryis best seen 4:...._4_--'_='-oD9 and _u,_O:',z:'.:cn""

presentdata for the variousorientationsof t?.erake at the nozzle exit

pl_ne. Figure D9, _Jnichis for the lowestaltitudetest eondition_shows

exceptionallylittlescatter. _gure D!O is for the highestaltitude.

The scatterin z.-.,edatameasuredby a gzven probe as the =_te zs _o.....ed

is :_uchless than the variation-_ff,th r_d_l____ __s,,_n__'__o _.

?me data from _'_e_,.individualruns are sho;,r,in FiguresDll -_,_r_..:_

s_5.

TA_ Dr

SU_IARY OF CALIBRATION TESTS

M = 3.S NOZZLE, NITROGEN

Run P4 T4 Rake Position Po To

Number (psia) (°F) X (in.) #I Arm Cpsia) (°F)

i B 7.80 3S8 0 Up 5.95 329

2 4.2S 363 0 Up 3.37 314

3 2.18 362 0 Up 1.76 313

4 7..70 354 0 South 5.99 317

6 7.83 362 0 North 6.12 328

7 l.S0 353 0 North 1.24 308

8 1.40 3S6 0 Up 1.23 308

9 1.38 562 0 South 1.17 303

i0 7.95 349 +12 Up 6.19 322

ii 1.56 317 +12 Up 1.29 280

12 7.78 319 -12 Up 6.06 298

13 1.38 511 -12 Up l.iS 271

14 7.70 325 0 Up 5.88 301

iS 7.68 320 0 Up 5.87 300

16 1.38 341 0 Up 1.13 280

i. P4 and T4 are static conditions in the supply tube prior to diaphragm rupture.

2. X = +12" is into _he nozzle, X = -12" is downstream of the noz:le exit.

3. #i Arm of the rake is identified in Figure DI.

4. No data were obtained on Run S because of a premature diaphragm rupture.

D-5

!'

- P_TOT A_i I _D_ALPROBE NO, DIST. (IN)

! 27.51 i 1I 27.0 '

2 !3 i 18.54 I 14.05 I 9.06 i 4.5

7 2 9.0

L 8 -- 3 3.09 3 12.0io 3 22.5

._i_ure D1. R_e Configuration.

D-6

1

- _. __.DS__., L._-._ .a_.,..I a._._ :,e--.,._G .!_ 7.d.15T.?_-_3 .LAP _"'

.. m ! 10 7-9,.,'1g, 1_ 90 U,.P +-[Z"

- _' f4 Z 701J:._3 _I0 ,fJ.# 0"'

• . , , . . "..

...... r-................. - .... -. .... _'7.--7".......... _i ................ :" -m.:-'.--r - .' ......... -:-"

..2.4--_ _ . . :: . . . _........ : . .._:- . ..... 4-'- fT" i':...... '" ---- .... "- --"--:-"_--:=" :":':':--'-'- 1:- ::'- _ : .......... .-:. : ."_-.,_" : -. .-

.... I ': __.- . . . o-, i- ,_ . - . . :- .-:-i..--i i _;_ :.-.::-- :. _I ' : : _. :• --; " : m : : -:.--.:---_i'.-gk_ --_-i_-_...... i-_--;__.-:- ...... --c- ;--_--._E- :- ........ " • --_-'_ ...... ---_------_ _- - -.--- _ ..r'_--..... :................_..... _.:_,_...... ,__.: ___._.__,_.... :___.__:_._-_-,:..3_....._,__..,• ' L = " • ' .... : ' :.- :'--'- ' ' ":"._ ....-.,,__ .... -._..._ ,-, _. -- ..... --.._.L._.___..____

.:Po . - .... 0 : :g : . • .. i.. :. i"'--i-?, ..:V¢i._-- F ........ - ....'--_:::-:: _ -:7--7 ....:. -. -'7:-- 7-7- --- 1.7--._'-/--:'.r .2a9-:_ :: .... :: - .: ,. :. -, r - , , . [

-.i.i .... ,._ . -- ..................... !.__.C .... :.__-.z-..: ..... --_'_7_.:..C_.. " " -'---.... .-) i " :- ' '" . " i i " " :.' : . : '-::!: : ' r-:

' ! i._- ........ :...... :........i...... ---- ....... _-.--=-.- .... !_--: ! .-:i--.:--::-...... L .... _ __ ,_

- .=-. ....... -_ ..................... :'.................. "_.... __ ........... L..:..:__-:. :_ . ;. .i .' "_ ' : . -_- . ." . . _ _.- .'--" • .

_£'7=".7 :- ;-_ ........ r: . . •.................. -':-. .... ......-:...... i .... " • "" " ; :-• _. r : _.:........... ___._ .... ._._i'.___ ....... :........ _ .... , . _. :- .... . . - . . : -

-_-_-_::_i-_ -_ :--,._r-i -. .-,- - :.., -..- - - "-. -.___-7__ ...a_ -2 ...... :-L'"'":,2 .,,- '" .... __-., ' ._ "_-:: - .... m .... 2....... :" " " ._ .... - ..... '..--_..i-_--.-_:_, _, _: • : , - ......._ :i -. _-.7- • ..-..c_:-:i-_-:-.-+.:._,..:L-_-.7.m-_"" 77-:--_--_- --_ ---_.:_ ....... gT-.--_-:-i.---.:_-.@..:P.:....!---f+-4_l_:_......_. ....'_'--:.::i--=-:._:h--!----.:'_ : ...... _r --_I -i:"i.-7.; ! " :.%_ :-_i : .:_---, :,"! -- -.: ;

.... i. -- : Z'.': ".. L... " ......... ' "._-_ J..... .2! ..... ." . . , .-_.-. -1

...: : .: :, :. 1- _ ---i--.-.-------. ........ a._.J ._ ....: : ... - . , . ;. - ., ..

---:Faa----'---. -...... =-'.'_ _-_--:: ....... : :-- --r- - ".'" : :": " . . . :........ .-,:": : .... [ i "' " " " 7 ': - " : " :....... "' ' "

.... :.... ,. a-iZ "'_ '_'.......t__:!-" -. .... ' ' ' "0 .,.!,. 8 fg ,_ 20 Za- Z8

! Radial Distance (Inches)

- Figure D2. 100K Foot Altitude Calibration Data at Various Rake Positions.

D-7

P_,,_!_.,,,__,,t_:_i _.__,._F._ . G 7. l.foli.2.a- _3o z t. - O" _

.... o 9 1.3,_11,17 IOa_l I:_-_.ia.z__Lzo..u.p[ 7-27'__

.. 0 13 t,,_&i l,t$ !0o u.Pl -I'_".......... o w_ I.a___8!_--!?too_I 6"................ T"

4,--_-- : : r : ! !

." ..... U "-_'- T'--':. _" ----'_--_ .... '1" : .........

. . ,..-.,.o............... ,..- .:.... :. ._ ,_.: ..... . : ....

• _.A....... _ .............. _ :

_o:_o_..-.._:g,.......L-:o_:..:_..:_:_ • _ ...........o,20 A.: _ - & -

: , _ --! : i

- -"T" ......................................................

1

.,/_ .L___ : : : ' ; " _

i

_.z,L.............-_ ....... -, .................... -....... A- _Pt---_,,-- -'--" O ..... . -" "

:- i :'-;'_i ....- ' -: ....:_ _- :- _,-y-_: • : _- .....................• - -I :............ - : ..... !"--_.-'+ .... " -- -: ............ :

i

.- "..i .......... _.. .... -_:.:................. -.............

..... , ...... " .: ./Po . .Z. -

0 4- S 12.. /_ 2_, 2. 28

Radial Distance (Inches)

Figure D3. 14OK Foot Altitude Calibration Data at Various Rake Positions.

D-8

'Gi.... _ i_.j8 r._I t3o u._ - o"........ __,. _.L_L.'_':_al'90 '_J-_?.__°'_.... J___

.................. _ ......... - .............. _..: .................................. ,-:

-__:-i-:......::_:! _- -"-: -:'- ..............i I:- ......;-'-: :-:--"7::_'-_. ....... ' - " :--' : - - --"f

_:..__.-. -:-- _....... _...-. :- . 0........'" _ : _t :-"-: "_'-"............................. " " ...... :-.2,?.;_. -- ..... --"_:2 Q ..............

• t "; ............. _ :, .... :,............. 1

,b_''. G : ,_ : :. " " _ _ • :1

I-_i_ , "!_ -.-:---

.L___ .-........ _ ....":-....:. " .- --.:................ _ -.. _"

: : .- :. .............. _. .q. i .... : .... '-.. . : .....

. .-;....... _ .......

....... : -L ..................................................... _ ....

i- : .:- ,}.......... : .... _.- ........ ...._.._ :.........................

•"__"_--......................... • : _- ......... -mi- -

-/',F-+....... _- e,....... :-" " ........:-: ......' :o.......;......: °--_;4-:- : . : .....

.!............_:......• .__- ............I

.... I "'- : ......... : -" --; .............................

.. ! _ :

......-I " " ' .i


Figure Dh. Calibration Data at Each Altitude "Jitha Fixed Rake Position.

D-9

_ _-=.............. !,_v_:_u_ip_ F= P_.i_- _AT. ;• .© _1 _,f_ .... i. 'Psi&!pst&;z_ _,,_ A_.DIST_

• "o_-z,_r,,t '---.... .. : Q ;. 4--_7..70s_'_ _0 ,__. i..... 0'" ._._ ".... O"._IAP._ ..... : ' ,_ :.q _1.38 f.17'foo_ G ! 0" ,

.i I t -0 . . : ........ _ .....t

- i" - " . . ;" . - " .....

o_, ,[t

...... _ ---- :'---:---_==.---_--'-r_"-': .......... _ -:---!'-: -=;--- •

- . .... - ,,_ . : "_ : ;

• ,. -! - i._--'-c_ , i - if::- o-• ,_",, .............. 'r- • -.': .... . -- ......... :: - --": :- -- ........ r .....

_z_.__.... _ o_........___..........._, _---_......:...._ _...........#_ i ........ _.. - _ -_i: ........ :__,.,x ! ....... . . 2 .......... a_ .

-;Z-_4 : :: :• 'i ............. : ............... ! ...... -- ....... i...--: ............

| ..

t

,"....... T ....

3.6 .................................................

.._____2.... 0 ..... : ..........

,!-:_..:,.. ...... _. _: L......O-....o -- - • • .........................................

i :

i : :.f __ :__

i -t

:a., .._ , ...._:.__.... _' .4, ,_ _z(__.,)...i-._' . ............. I i , .; ,

o 4... 8 tz ,,_ 20 z_ 'z'8Radia! Dista_uce(Inches)

Figure D5. High and Low Altitude Calibration Data at a Fixed Rake Position.

D-IO

.hO*I'2ARIv_ ' 0 g 17.83 _.t2, e!5" . NI _ Q" .:--i

................ '- " ' ; - " _.................. _._c'"........ _'3_.R_. ......... _ & ! 7 .I._0 1.Z4:130 _ N i ....

; ?

"'- . ": ...... :...... .':'--'- "" """i- ?.-?- ..... -T---: .................... .- _ ............

--,I._. • . . _ , : : . .f . , ; _ : • ". ., . • . ." . .: .

;; .....----2_:;-;-:.;__;_-;." i ; :...::_.__.:._=_L: d: ---'-.o

,-Z_ _..... " .... .O...... ""-_ -_ Cf .............. --'_c_ .....

Po" : • _ _ , ._ : _ :-_'0 . ....."..-:.A..............:.---.-........ ":.......... " - ------- -A-:o.

• ... ............. .__............ - .............. '.. .'." :I

I:. -.4. ......... " ...........

", :. :.-----of-- o...... _e-- --- o

-3._-: ----&--_ ...................k ................. '- ........ i" ..... __"................

i............ ". . ql N ...........

•- I 7. .

' e _; .__=: ,... ...._, _ __ • _.! :_;,o,) , ,0 4- ,_ /2. /_ 20 "-.4- 2,3

Radial Distance (inches)

- Figure D6. High and Low Altitude Calibration Data at a Fixed Rake Position.

D-f1

3y_.MiRUNp+ Po i_rTr :,£a_:,:Lcc4r._

"O_'Z_,R_ -.:_ I o ,..IO 7.._?.5"!&iq;qo _ _P: +-',2." 'o_*3xp-r_ ' _ It{ LI.y_ s.2q:_aoTu.p:.ix,,'_

........... 2"

.! -

• . "L_ "-7 ......

t i • : ...... t" : • . , . .

• "'1 - " :'- -T ..... -- : =_...... !: -:--:------=-_--i .... .---- ............ " - .:.- .......... :, • i • . i''-" _ • i" " A_ " " ..

" i _ ...... " :i-:-=-'i "_-:" ; '-: ..............:" -- t i-_! :- 7........ :--'_ .........T G.. "

'__ -"..... ' ----"_" 0 • _"..............p jl " :O-- :......... i=.... (_.._= ..................

.- . _. _ ................

P'_..I......... :" ......."...... ,,, : '_,_o.'--.-..-L..... :........... L_ : .;

' - !" ": ......... ".... "7.......... :' 7 -...... "-'-" " : .....!..... ¢ .....

...... ! .....

...........: = -i' ...." :-7 ...........:--1 .... i.....- i4 " " " = .........

.u _ . : L........ 2...... ,!-'_ • • , ;. .. i : ',

-?. 6-_- : : ,_ ..................... _- ....... _! & -- .: :- ..... " -i-A " " ..... A.L

i.... _,. -.::_.. :..._ 2:: o-=- " • : "_.4i : .....-- - " - ' " &.

i---:---'- ...... : .:___ _. -.1_._. .... " .._ -i............ ! ..................... - .-'--'T ....

--.- , . : -.... . ........... ......... ,} ............. _ ....... -- ,.--. : _ ....... 2,.2.- ...... " .......

_._ I ..... :.... :-..-2' ............. : ...........................

,; .... 8_........ i...... - ' . ...: .4-.... • a. (&') ..z ,• ._L_L : " ; ' : i - " _ • :0 4. 8 12, 16 20 Z+ 2_


Figure DT. High and Low Altitude Calibration Data at a Fixed Rake Position.

D-12

-:-. :.:. :. ....: 'SLM.!_,ON:P.t-P,_ : P'r _RAk:EI._C:A,T-.:

....o_3.ARM ....: 0 IZ 7.7a 4.0(_ ioO: _-P -12."

........ o*_Aam [ a.: u _.3a.r.t,y _ca_u,:_..._-}:z.',.i

- I ..... " :' "*"" ; :.. " _ .-" " : i

" f'"- : --i :-"-_-::!--o:-:....--_-----'.-7---:_::-:-.....-"., ' ....'----_! :_a;_--; . . ' _::"...._:g.: ""....7:-: : " _--!_°'_ " a: _ : , .h_._ ': :: : .- 1. ......" .- -' "-..::

-_o..... .--_:i .... T-., -.-......... " : "/ T'-" "°- :j :.. o.: - •

" '::'-i " -" _' " • ., "F-":-:'-'_..... :..... " -'--'-'L" : ............. -": "--:.. : .-- • .. -. : .." : ._.

; : • . .• . . . . . : : : :

i ' . - : i -. _ " : - . • : " :" !.45&- ' '' • 'r ; ! ,: ; • ' ,, •

.I ; ". . . :. _. . i '..i : . : . • .

.."':" "'_:..... :' ":"" • "T---:. -"1'.---_... ,'""---"_'_-...... :- - ; .... _...... : ....;. ..-. -°-..:...............................". . . . . ; . _. .... .' "" _" " : "_ ":i " "! I . "--"" : • " • ' "- ""i." '" t ::. . . ,..-"!.n'" _. : : "" . . . ' i: ' ' -_::-:I......-......---._--,-_.-._--. -:-......,, ...........----,...... : ......

• _::, 1!" " !:.-.':,.r" " "::'" ';":'.'-::! -!: ;:" " • " " "":' : " i " :

:--- .--T'-_-Z---:-....-:- --i'-:-_:-"-:".-_.: ...._-::-:"- ' ' " :

. .I . . : .. • - :-

[ i: : ..... ..... ; ..... :...... _-" ........ t _" :"--':": ..... ! .... "--- -'- - : "

_.t. ": :"-,_:" "" ;.....7 ' "'" '!"":: _" :

..... . -: . ,. :,_ }....0 4- 8 IZ /& 20 1& /,3

RadialDistance(Inches)

Figure D8. High and Low Altitude Calibration Data at a Fixed Rake Position.

D-13

_'l"tw, RUt_! P_, . Po 'PT 'RAKE' LO_:..A,'T'..;

i_.Q.I 18 . 7.8 ._?_"4.oo a._ : . . 0'"_....._,_._;7.-_._- r.a%__.5.....o'"• El 6 T.83 g. II 95" N 0"

-- _ ....... -_ • ..: ". : .................................. : --

,Z4-, ' .......

.,'....i........: .-:--? :--;_T;---....;-:-"-....:_1;.....: - .....:

" - -!*:..;;k-:_--,-_ : _-".2"_-4..... . _- Q_ __ . . 0 .............. _......... *"rl .. _..

_i_-......._ _ .........._ :-: ....... __.__P_ ............................ -..2__: ...................... .

1..... .'. ._.1....... :....... =........................!

Q

:)i i :::i:: ...........:----3._;-;;--;.;----:.F.__-_2--,"._"';;---_'-'.;-+L.L_;;;.......;" ';

;:;::--::::::;:--.....-:---:":•-I...._..:.....:;.__;__.;_,_-_.:.--_-.-.._--2 ;IT;"_--T.-:.i ;..--.:;

I "

-=-"-1-:-- -_ ' 6 .__...L..,f_.-.... _----_ ' .--_ m _. ,'Po9-...z _:.... _ t i ," " _ i ; I • _ " I t - _" :

O 4- 8 lZ /t_ 28 24- l_.Radia!Distance (Inches)

Figure D9. Flot¢Symmetry at 100K Foot Altitude.

D-14

'_YM:I_uNIP4-_P_ ..P'r:_kE ZeCAT,,., -_ ! ...... . . ....

_. 'pSto,.__t_ _ H9_ _._ A._._ t_:,_.I, G.' _. ;. 1.40;I.'Z3 roo u..P 0"-. ii A : 9- ' r.58. i.l"t ioo ,I-.r..- O:'

[)_;i;-:7-_.soi!:_4.,3.o,,_--- o"............. ...

.. : . - ..... _ .... 7 - ...... .." .

...... :;"- ...... _"......... i ....... ---_ ...... ":'-.............. : ......... .._"...... "_ ._.... ' :--___ :____.; " '. ".................. i.--":.l_i. " _ : ::. _ ! . _ _ . , : i . • : _ •

- :,i :-: ....T= i..... T:-_i--_'.--:------ .......... :-": ......-- : .:::i7:!"Z-'-r--.......... ,'----.... _-----.---....-----...................

"-_ ..... .-- _-- _---.--__:_......_.---_--_-,--- _.....! ......:m • :-.' :,;_-4- ...... -- -'_:.......... _,D• : . • : -,.-., . : . :

.... p' .............. '- --- .- _. - .... ----.-I..-- ........... ...... - . : .... : " -I. " .----A

-- / | " • -, . . : • ]

.2..__......k......... _, ........... ' : .r-.....-,_....... ¢:_Po ,_. ..... -_-._-. ......... --.:_-- - .... 2. i...... ;.... :- ; _'

: !

_-_ : .'0- • : :-: . : ®i "-2 ...£'.--..---:- .... ::- :.,.... " " ..... .

i ; -" .. : : ."I

"- k . ...............-....--!-::--i----; ......... -- ;-_B " " I ' I _, " . "....... . ..... : .-. ........_...... ..:__................ __.... :_ -_.._ _._.-."

1..... ; . - . ._. - ..: ] " .

"-" t 11" -7 ........ t-'_;"!-" ...... _ ...... : "-';;""" 1'..... :" °" : ...... : "' ! ......... , .. . ,

__,_._--. ' __• .f .. 0 " ' " i ... ........ - .... -Oi-:-"

: - i 11;2 -:........ : ..................__!......... :-:-----?=':_......L- ......: -:" -_ ......._ ' .....--_.4._ .

...... t..... -..--2:::.-_ .... =..2._'..2-:2....... " ...-..--..-.i--"..... : - -" .... " .I i

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

.- ..... - . 4.. ..... _- ; tO 4- 8 12, l& 20 14- 18


- Figure DlO. Flow Symmetry at 140K Foot Altitude.

D-IS

......... _ _3_ _.. . _....................... ........................

" " -. T- .......... " ..... - ' - ...................

- ' " ---.-L. _ .:L._.:_. :_-'_--i.--- 7 .j ........ .-----r ............................ -- t ,.._ : _: i"

' I ". : ." : '. i ..............................._. • ...... :.... (D

;z:_ _ _ i _-7 ,.o ................................ -__".._. _ .... __.-................. :.-__= .......... _=._.__o';" o • : ..." ........ _._--._.Po!

• .._........ ,_ .--. • : .......

I -

•_i...... _-: .... - ..............• .. i_.... :. ...... ............ _....... : ........ i..... i .........

_%-:;_-.-_!.-........--_...i-L-_-:---:,-:........:-....:--_-::-;-...re'V--" ,----:- O, :.. : , " ..... '- ........... 0 ....

1" i -.-__. L ... L_-..: :.......... :'- :--_- ............ O- - "... : ..........t. " .... : "

-E4-, :. _- .0

,.. ?_._i-.:._ ....L . .:_..... =: ............, - ...........-I ' : !

..

-.:-i...... : _- :. - ;Y-7'7-!--:.... _.... "........... i...........::_--_:! _, if_.- - ..... ......._ ?_-7._.......• " .... : _. i : . ::-i

0 4.. 8 12. t_ 2G 2a. '1 8'Radial Distance (Inches)

Figure Dll. Run 1B Calibration Data.

D-16

r_ _,J Ag _ .-,

" 0 : I :_.li 3._7_ZlO.J._ , 0"-_Z A ;__t .... s. .. , . :

.... T.......................

"-j : --: ..... -: ; .......'.-.. 7 -:-'i T Y: ,_- --- "

'--.. : ...... .-_.A. ,___ "___...... . ............ ._..... -_" k o , O : _ . ............... 0 : :

i ' : ' : Q- " .0.Po... ...... ,., ........ _....... _L . iz.... _ ........ ......... __'-..- ...... _._

_.=£ff_- _ ! ! .... _ ;.|• : . ! : : ; ! ...... _ ....... . ......................................................... _-_

! . ." ;

..... _. .............. : ........ : . .. : ..................... !....... : .1

.I,:3_ ' i J '' _ ;

- -- -................. _- --.......................................... i ........ • • ; . ' t .

i---._:-6,_ -............ . .............. " "

"_. ."

......." ° ...... .... - ° ........ i ..... o_- _ . _ --.-;...................J -L; : '.-- - ....

• - : ; • i " "

..... t--:_-i......., ._...!-...._.:..___........__i. _.. :.................° . _ , . : . - .°

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........• _ -- -.---_ - . . .

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o 4. 8 IZ I_ 20 24. ZRadial Distance (Inches)

_ Figure D12. .Run2 Calibration Data.

D-17

r

•o ,_1_RM ..... _¥_v_.t_U_...._-_.,,: Pc ; ?T ,_K: '"" -........ _ O._to.pS_a,_ H_ '_._.a_,_Ax. _ 15"r:'.,

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_ 8 12. 1_ 20 14- Z,gRadial Diste.nce(Inches)

Figure D13. Run 3 Calibration Data.

D-18

! ......;_VM,R,dt_ P4 Pc, :_PT _K _-/.cCt:-'9"_I AR'_'{ P.tja Ds_e. _.t/o _:-l_m _'_. 3,5 7"

: 0 zL 7.7" 3"_'q_ 130 _ j

...... _ .................. L_._ -4-........... _. _._ .................

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n

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: 0

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!+ 8 _z i& 20 k4. Z8


_ Figure D14. Run 4 Calibration Data.

D-19

© ._IARi_ ; :ps_e._s-,,1.'.&H_._,_Av,._.!£,-!. , B

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RadialDis=ance(inches)

Figure D15. Calibration Data.

D-20

7

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. . . ........ . ............ . ...... , .......

---- 1.8 _ ' "........... _ °._.

r

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.. &.. Q

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0 4- 8 It I_ Z_ Z_ 2.8Radi_l Distance (Inches)

- Fig_treD16. Calibration Data.

D-21

:.SY_.RUN P4.- P,:a :pff-, RA_:5 LCCA_.[

.& _z.,,_,-..t ; o 8 rA.-o,l.z3 1o0 u..P 0"...... r- -[ . ! : -- ,

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....... :_ -_. __ ....: .-f .... : ..... ; ............. : .....

z8

; &._ . ................................

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t

i .... 8.g_ ....... _'-' Z 4-.... 4 joa. (,_') z.I" • : i [ : :

4- ,8 ;2.- I_ 2,0 Z4.-Radial Dista_uce(Inches)

Figure D17. Calibration Data.

D-22

0 _t /i,R/Vl _p...<i,_l::>.*"s<:l.u,.t_o-:_,_,i /I:,:;._,_ 7:.

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Radial Distance (inches)

- Figure D18. Calibration Dat_.

D-23

• I

.................... t ,-: I0 7._'f:g. lq 90 '/./-P ' +[Z" ],'aI_ZARM _ _ ' .... ' : ' r....._-I13 /_ R r,4 ! _ _ ' '

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...... ; ......................

• [ ....... ___...........................r .E2 ! . _ ,0

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-- : ........ - ....... I "

i '7 .......................!

I I0 4. _ 12. /_ 20 2.4- 2.8


Figure D19. Run lO Calibration Data

D-24

• ._ .d,_ ,..,T'. ,'5"_. R,,./t_ PC. po i .r_.. _R4_'5 "".... ..... _to, _.sto.',_ l-t_ '_4_H ":_. _!5, _,

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t E_ • . .... E301

t In ............. 0 ..... ......._4, •....................... _ ........1

! ....

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,o 4. 8 _2, : _ 20 !4- Z__adial Distance (Inches)

Figure D20. Run ll Calibration Data.

D-25

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0 4- 8 12. 1_ 2C _.4-- 2.£Radial Distance (Inches)


D-26

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0 4- _ IZ l_ 2._ 2.4. 2_t_cl.±al Distance (Inches)


D-27

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Radial Dlst;ance (Inches)


D-28

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o 4. 8 {2. l+; 20 z4 z9Radial Dista_nce(Inches)


D-29

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0 4- 8 12. f_ 20 2_ Z,9



D-30



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