F_ mZ:M"_eE _ P-4 RTR 174-01

EXTERNAL TANK AEROTHERMALDESIGN CRITERIA VERIFICATION

VOLUME I

May 1990

Prepared by:

William K. Craln

Cynthia FrostJohn Warmbrod

Contract:

NAS8-36946

For:

National Aeronautics and Space Administration

George C. Marshall Space Flight Center

Marshall Space FHght Center, Alabama 35812

https://ntrs.nasa.gov/search.jsp?R=19910001724 2020-06-28T18:06:06+00:00Z

I=_ E I_/1-1- E C I---I RTR 174-01

FOREWORD

This final report documents the ET thermal environment generation work

performed under the ET Aerothermal Design Criteria Verification study (NAS8-

36946). The work was performed for the Thermal Environments Branch (ED-33)

of the George C. Marshall Space Flight Center (MSFC).

During the course of the work significant results and progress were documented

in the progress reports submitted each month. The purpose of this report is to

summarize the thermal environment generation methodology and to present a

comparison with the l_ockwell IVBC-3 environments. The report is presented in

two Volumes. Volume I contains the methodology and environment summaries.

Volume II contains the plotted timewise environments comparing the 1LEMTECH

results to the Rockwell IVBC-3 results.

I_ IE M -r IE C I.--I RTR 174-01

Contents

VOLUME I

1 INTRODUCTION

2 BODY POINT DESCRIPTION

3 TRAJECTORY

4 HEATING METHODOLOGY

4.1 General Discussion ...........................

4.2 Undisturbed Heating ..........................

4.2.1 ET Nose Spike .........................

4.2.2 LO2 Tank, Intertank and LH2 Tank .............

4.2.2.1 Shock Shape ......................

4.2.2.2 Surface Pressure ....................

4.2.2.3 Laminar/Turbulent Heat Transfer

4.2.2.4 Boundary Layer Transition ..............

4.2.2.5 Rarefied Heating ....................

4.3 Disturbed Acreage Environment Methodology ............

4.3.1 Proximity Amplification Factor (Hi/Hu) ...........

4.3.2 Surface Roughness ( H,o_____k._'_H.=oo,h/ .................

4.3.3 Intertank Stringer/Waviness Factor (/Lt_g._\ E,mooth ] ........

H_i ht4.3.4 Flight/Wind Tunnel Scale Factors (_)

1

2

3

4

4

4

4

5

6

6

r

8

8

9

10

11

11

12

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i_ I_" M --r i_ C i,--i RTR 174-01

5

6

ASCENT ENVIRONMENTS

5.1 Timewise Environments ........................

5.2 Environment Presentation .......................

REMTECH/ROCKWELL IVBC-3 ENVIRONMENT COMPAR-ISON

6.1 40 ° Cone .................................

6.2 L02 Tank ................................

6.3 Intertank ................................

6.4 LH2 Tank ................................

7 CONCLUSIONS

REFERENCES

14

14

15

16

16

17

17

18

19

2O

oeo

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I=_ IE M -1" E C l--i RTR 174-01

List of Figures

1 30°/10 ° Nose Tip Body Point Locations ............... 21

2 40 ° Nose Cone Body Point Locations ................. 22

3 LO2 Tank Acreage Body Point Locations .............. 23

4 Intertank Acreage Body Point Locations ............... 25

5 LH2 Tank Acreage Body Point Locations ............ ".. 28

6 Light Weight External Tank Assembly ................ 34

7 Light Weight Tank Design Trajectory Altitude/Velocity Profiles. 35

8 Light Weight Tank Design Trajectory Angles of Attack and Yaw . 37

9 ET Conical Shock Wave Angle as a Function of Moo ........ 41

10 Surface Pressure Distribution on the ET at M = 3.0 and 4.1 for the

LWT Design Trajectory .......... .............. 42

11 Mangler Factors for Laminar and Turbulent Boundary Layers for

the ET .................................. 43

12 Example of Interpolation/Extrapolation of Hi/Hu for Phase I . . . 44

13 Intertank TPS Design and Surface Finish Details .......... 45

14 Intergank Crossflow Region Definition .............. -.. 46

15 Comparison of Maximum Heating Rates for Acreage Points on the

40 ° Cone ................... .............. 48

16 LO2 Tank Acreage Heating Environments (350 < XT < 600) . . . 49

17 Intertank TPS Configuration ..................... 51

18 Intertank Design Environments for B.P. 7355 ............ 53

19 LH2 Tank Acreage Heating Environments in the Vicinity of B.P. 1401 54

20 Maximum Heating Rates in the Vicinity of B.P. 7694 ........ 55

21 Hi/Hu Data Base for B.P. 7694 56

22 Circumferential Heating Distribution in the Vicinity of B.P. 7931

and 7935 (XT _ 2058) ......................... 58

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F_EMTEC i--! RTR 174-01

23 Hi/Hu Data Comparison for B.P. 7931 ................

24 Hi/Hu Data Comparison for B.P. 7935 ................

59

61

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I_ I_ M-I" _: C I--I RTR 174-01

List of Tables

1 10°/30 ° Nose Spike and 40 ° Nose Cone Body Point Locations . . . 63

2 L02 Tank Body Point Locations .................... 64

3 Intertank Body Point Locations .................... 68

4 LH2 Tank Body Point Locations ................... 71

5 Light Weight Tank Design Trajectory Parameters ........ ".. 76

6 Methodology - Nose Spike and Nose Cone Points .......... 82

7 Methodology - LO2 Tank Points ................... 83

8 Methodology - Intertank Points .................... 84

9 Methodology - LH2 Tank Points ................... 85

10 Rarefied Flow Sharp and Blunt Cone Heat Transfer Equations . 86

11 Typical Example of Hi/Hu Input ................... 88

12 Typical Timewise Thermal Environment ............... 89

13 Maximum Design Heating Rate and Load Summary ........ 90

14 Aeroheating and Plume Convection Max Heating Rate Summary

for Body Point Locations XT >_ 1872 ............... . 106

15 Body Points at which Environments did not Favorably Compare

16

Between RI IVBC-3 and REMTECH ................. 108

Overview of Net Spray Application Tolerances ........... 109

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I=_EMTEC I---_ RTR 174-01

Nomenclature

Symbol

f

H

HCNV

Hi/Hu

HR

HU o

INTRF

M, MACH, Moo

ML

NL

NT

OT

OTS

P$

Poo

QDOT

Qr_OAD

r

RF

Reinf

Ree

S

Decription

Wind tunnel to flight scaling factor f = (Hi/H,_)_d

Heat transfer coefficient, BTU/Ft2sec °R

Cold wall heat transfer coefficient (HW = llO BTU/lbm°R),

lbm/ft2sec (see Table 12)

Interference to undisturbed heat transfer amplification factor

Enthalpy based on boundary layer recovery temperature,

BTU/lbm°R

Clean skin undisturbed heat transfer coefficient for aeffective =

0 deg, BTU/ft2sec°R.

Interference to undisturbed heat transfer amplification factor,

Hi/H=. Tabulated data (see Table 12).

Freestream Mach number

Mach number based on local conditions

Mangler transformation factor for a laminar boundary layer, see

Figure 11 and Tables 7- 9.

Mangler transformation factor for a laminar boundary layer, see

Figure 11 and Tables 7- 9.

Shuttle ascent configuration consisting of the orbiter and exter-

nal tank.

Shuttle ascent configuration consisting of the orbiter, external

tank and two solid rocket boosters.

Local static pressure, psf

Freestream static pressure, psf

Cold wall heating rate along the ascent trajectory, BTU/ft2sec.

Integrated heat load along the ascent trajectory, BTU/ft 2

Recovery factor, see Section 4.2.2

Roughness factor, see Section 4.3.2, Tables 6 - 91

Freestream unit Reynolds number, F'q"

Reynolds number based on the boundary layer momentum

thickness.

Boundary layer running length, ft., see Section 4.2.2.3

vii

RTR 174-01

Symbol

Too

WF

XT

Decription

Freestream static temperature, °R

Waviness factor defined in Section 4.3.3.

External tank axial coordinate measured along the centerline of

the tank, ft.

Greek

O_etf

Ot

A_

A_

0,

8T

Poo

Angle of attack in the body axis system, nominal design trajec-

tory, deg.

Effective angle of attack defined in Section 4.2.1

Angle of attack with negative dispersions, deg., (see Fig.

Table 5)

Angle of

Table 5)

Angle of

jectory, deg.

Angle of sideslip with negative dispersions, deg., See Fig. 8,Table 5.

Angle of sideslip with positive dispersions, deg., See Fig. 8.Table 5.

Angle of attack dispersions, deg., see Table 5

Angle of slipslip dispersions, deg., see Table 5

Shock angle for a 39.38 deg. cone, deg., defined in Fig. 9

External tank circumferential coordinate, deg., see Fig. 6

Freestrearn density, lbm/ft 3

,

attack with positive dispersions, deg., (see Fig. 8,

sideslip in the body axis system, nominal design tra-

viii

i_ E r,,_ -1- E C P--I RTR 174-01

Section 1

INTRODUCTION

The Thermal Protection System (TPS) for the Space Shuttle External Tank

(ET) is designed to maintain primary structure, subsystem components, and pro-

pellants within design temperature limits. The three thermal protection materials

currently used to protect the outer surfaces of the ET are Foam Insulation (several

types), Ablator SLA-561, and Ablator MA-25. The type, location, and thicknesses

of these materials are primarily dictated by the level of the aerodynamic heating

environments during ascent flight (lift-off to MECO). The ascent design thermal

environments for the ET were generated by Rockwell International (RI). This set,

referred to as the IVBC-3 set, [1] is composed of the time dependent definition

of flow field and heating data for 679 surface locations on the ET skin and pro-

tuberances. These environments reflect the most up to date wind tunnel results

(TFL97, [2]) as well as flight heating measurements from STS 1-7.

The objective of this study was to produce an independent set of ascent en-

vironments which would serve as a check on the Rockwell IVBC-3 environments

and provide an independent reevaluation of the thermal design criteria for the Ex-

ternal Tank. Design heating rates and loads were calculated at 367 acreage body

point locations. Ascent flight regimes covered were lift-off, first stage ascent, SRB

staging and second stage ascent through ET separation.

The purpose of this report is to document these results, briefly describe the

methodology used and present the environments along with a comparison with the

Rockwell IVBC-3 counterpart. This report is presented in two Volumes. Volume

I contains the methodology and environment summaries. Volume II contains the

plotted timewise environments comparing the REMTECH results to the RI IVBC-

3 results.

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!=_ E M -T- EE C I---I RTR 174-01

Section 2

BODY POINT DESCRIPTION

Ascent heating environments were calculated at acreage body point locations.

These locations were broken into four categories: (a) The nose spikes and nose cone

(327.25 < XT _< 371.0), (b) The LO2 tank (371.0 < XT _< 852.80), (c) The intertank

(852.80 <_ XT _< 1125.15), and (d) The LH2 tank (1125.15 < XT _< 2173.02). Body

point locations for these components are shown in Figs. 1 through 5 respectively.

The individual XT, t_T locations axe defined in Tables 1 through 5. An over all

sketch of the light weight, External Tank configuration presented in Fig. 6.

RTR 174-01

Section 3

TRAJECTORY

The ascent aeroheating environments were generated using the 1980 BRM 3A

3_ Dispersed Light Weight Tank (LWT) Design Trajectory. It is based on a De-

cember launch from the Vandenberg Western Test Range and incorporates a right

quartering head wind with s and fl dispersions. The trajectory data consists of

the altitude, velocity, angle of attack (s), angle of side slip (8), ambient density

and temperature, and the As and Aft system dispersions from lift-off through ET

separation. The tabulated trajectory data is contained in Table 5

Nominal trajectory s and fl values were combined with the As and A]3 dis-

persions to produce the worst case envelopes as follows:

s + -- s + As + (3.1)

s- = s - As- (3.2)

/3 + = ]3 + A/3 + (3.3)

f/- = ]3 - A]3- (3.4)

The altitude and velocity profiles for the ascent thermal design trajectory as

a function of time for first and second stage flight are presented in Fig. 7. The

nominal and dispersed angles of attack and yaw for first and second stage flight

are given in Fig. 8.

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I=_ EE M"I- EE C I---I RTR 174-01

Section 4

HEATING METHODOLOGY

4.1 General Discussion

The procedure used in calculating the ascent convective heating environments

on the ET was first to calculate the undisturbed body alone heating at the flight

conditions, then to amplify the undisturbed level with interference factors. The

interference factors are a result of shock wave-boundary layer interactions, effects of

mated components (SRB's, Orbiter) surface irregularities and protuberance effects.

The undisturbed heating was calculated using semi-empirical flat plate methods

converted from 2D to axisymmetric body by the Mangler transformations. The

interference factors were determined from wind tunnel and flight test data.

4.2 Undisturbed Heating

Ascent convective heating environments were generated using the LANMIN

code [3] on the 30 ° conical nose tip, 10 ° nose cone and 40 ° conical section of

the LO2 tank. Heating at the remaining locations i.e., LO2 tank, Intertank, and

LH2 tank, were generated using the ETCHECK code [4] developed at REMTECH

specifically for the ET ascent phase of flight.

A summary of the flowfield, laminar and turbulent heating methods used for

each component of the ET is presented in Tables 6 through 9. The rarefied heating

methodology, based on the work of Engel and Praharaj [5], is presented in Table 10.

4.2.1 ET Nose Spike

The nose spike is composed of a 30 ° nose tip and a 10 ° nose cone afterbody.

Shock shape for the spike was determined from the 30 ° nose tip i.e., a 30 ° sharp

cone while the surface static pressure was determined from the 30 ° cone for the

nose tip and a 10 ° sharp cone for the 10 ° after body. Turbulent heating was

calculated from Spalding-Chi skin friction correlations and laminar heating from

the Eckert Reference Method. AVon Karman Reynolds analogy was used to

calculate heating from the skin friction relations. Flight path angles of attack and

yaw were accounted for by resolving an effective angle of attack:

4

i=_ E M --F E c i-.-! RTR 174-01

aegective = --C_ COS8T q- ]_ sin ST, deg.

from the Light Weight Tank Design Trajectory dispersed o_ and ]3.

therefore calculated as a function of effective angle of attack.

Heating was

4.2.2 LO2 Tank, Intertank and LH2 Tank

As previously stated heating at body points on the L02, Intertank and LH2

Tank were calculated using the ET Check code. The procedure used in calculating

the undisturbed heating in this code is to:

a.) Calculate the undisturbed heating (ttuo) along the trajectory for aeff = 0

deg, then

b.) calculate the undisturbed heating at angles of attack and yaw by:

The ratio Hu/Huo is undisturbed heating at angle of attack divided by undis-

turbed heating at zero angle of attack. A study of experimental and analytical

data suggested using simple curve fits for the ratio Hu/Huo. Curve fits are also

used to calculate the recovery enthalpy ratio Hr/H_.o. This approach sacrifices

little in accuracy and significantly saves computer time. The curve fits for the

heat transfer coefficient and recovery enthalpy ratios are defined as follows:

HEAT TRANSFER COEFFICIENT

Nose Cone 340.82 < XT _< 371

Huk=l.0I"Iuo

(All Moo and c_eff )

Ogive 371 _< X r < 760.35

H_

- I + F(XT) _,ff (A11 Moo)Huo

where F(XT) = -0.07625 + 2.928 x 10-4XT - 1.2247 x 10-TX_

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!_ I_ M-F I_ C I-,-! RTR 174-01

Barrel XT > 760.35

H _ 1 + (.02404+ .01246Moo)_effHu---_--

H = 1 + .07388ae_

RECOVERY ENTHALPY

H.+CU_(sh 28,+,cos_0,)

C = 0.1998 x 10 -4

0_< Moo < 4

Moo>_4

c_T

? = .88(Turbulent)

= .85(Laminar)?

Again the trajectory dispersed angles of attack and yaw were combined into an

effective angle of attack for calculation purposes by:

aeffective -- --OC COS _T -}" _ sin ST, deg.

The methods for defining the heat transfer coefficient and the recovery enthalpy

(Huo and H,.o) for zero angle of attack will now be discussed.

4.2.2.1 Shock Shape

The nose shape of the ET is bi-conic with a 10 ° conical spike 13.6" long attached

to a 39.38 ° nose cone that is 30.2" long. Flow visualization data from wind tunnel

tests have shown that the bow shock shape is determined by the nose spike. The

shock angle is determined at each time step from a table stored in the ETCHECK

of shock angles as a function of stream Mach Number for a sharp cone with a half

angle of 39.38 °. The shock wave angle for the 39.38 ° half angle sharp cone as afunction of free stream Mach Number is presented in Figure 9.

4.2.2.2 Surface Pressure

The surface pressure for arty location on the ET body is calculated by using a set

of empirical equations developed by REMTECH that was based on experimental

and analytical pressure data for the ET. The analytical data that were obtained

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F_EM'T'EC P-I RTR 174-01

from MOC solutions for inviscid flow and viscous effects were accounted for by

application of viscous interaction theory. A detailed derivation and definition of the

empirical relations used to calculate the surface pressure are given in Refe.rences [5]

and [6]. Pressure distributions along the ET surface are shown in Figure 10 at

LWT design trajectory conditions where the Mach Number is 3.0 and 4.1. The

local surface pressure is a function of the local body angle (8,). The equations

used to calculate 8, for the ET body are as follows.

CONE 340.82 <__XT __ 371

8, = 39.38 (deg)

OGIVE 371 < X T _ 760.35

8, = tan -1 760.35 - XTr + 446.08

(deg)

where

, = v/(613.64)'- (xr- 760.35) 446.08

BARREL 760.35 < X T < 2058

.8,=0 (deg)

4.2.2.3 Laminar/Turbulent Heat Transfer

Turbulent and laminar flat plate heating methods are used to calculate the

skin friction and heat fluxes for the acreage points. The method of Spalding and

Chi is used to calculate the turbulent skin friction which is transformed to tur-

bulent heating through the Von Karman form of the Reynolds analogy. For the

laminar case s the method of Eckert is used to calculate the heat transfer parame-

ters. Mangler transformation factors required to transform the flat plate heating

to axisymmetric body heating are shown in Figure 11.

The equations used to calculate the running length are given below. The light-

ning rod spike is ignored and running length is assumed to start at the hypothetical

apex of the 39.38 ° cone.

CONE 340.82 <_ XT _< 371

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i_ E l,v,I-T-_- C i--i RTR 174-01

S -- 1.2938(XT - 336.62) (inches)

OGIVE 371 < XT < 760.35

S = Sx_,=371+ 613.64 [[c°s-z

BARREL 760.35 < XT _< 2058

7_0.35--XT _ 50.618 °61_,64

57.296 (inches)

S = SXT=760.35 + (XT -- 760.35) (inches)

4.2.2.4 Boundary Layer Transition

For undisturbed acreage points, the flight data indicated that transition from

turbulent to laminar occurred between the times that Ree/ML = 94 and 47. For

disturbed points, it was difficult, if not impossible, to detect when transition oc-

curred. Based on engineering judgements of all the data analyzed, it was decided

to force the transition from turbulent to laminar abruptly where Ree/ML = 47 for

disturbed flow regions.

4.2.2.5 Rarefied Heating

Rarefied heating to the ET nose spike and 40 ° nose cone was calculated us-

Lug correlations from Reference [6]. The methodology is defined in Table 10.

The switching criteria from boundary layer heat transfer methods to the rarefied

methodology was calculated as follows:

MooA=

Ze(Reoo)0.5

For A < 0.050.05<A<3.0

A>3.0

boundary layer methods are usedrarefied correlations are used

free molecular methodology is used.

8

RTR 174-01

4.3 Disturbed Acreage Environment Methodology

Approximately two-thirds of the flow over the ET is disrupted due to the pres-

ence of the Orbiter mounted on top and the two SRB's mounted on each side

of the ET. Early in the Shuttle program, it was decided that the aeroheating

methodology would consist of a reference heating for disturbed flow that is ampli-

fied due to various flow disturbances such as protuberances, attached bodies, and

rough surfaces. This approach was followed for wind tunnel testing, data reduc-

tion, environment generation, and flight data reduction/analysis. The calculation

approach is summarized below for wind tunnel testing and/or design environment

generation.

1. Define undisturbed heating (Hu) over a clean skinned unmated ET at a

prescribed flow condition (_, fl, V_, M_, p_, etc.).

2. Define the proximity amplification factor (Hi/Hu) due to the presence of the

Orbiter, SRBs, and adjacent protuberances.

3. Define amplification factors due to surface irregularities; roughness (Hrough/Hsmooth)

and (Hstfinge, ///smooth).

4. Apply any scaling factors (if applicable) that resulted from analysis of the

flight data.

The resultant heating can then be written as

H'-Hu(-_u) (H'°ush ! (Hstfinge') (__\ Hsmooth / k/'/smooth _,.HW.T. /

The undisturbed heating for a, fl ¢ 0 ° was further simplified in this study to

Hu = x Huo

where Hu/Huo is given by simple curve fits previously discussed.

This section will address each amplification factor and give a brief explanation

of their derivation and application.

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i_ E M -r i-.-.-.-.-.-.-.-._-O i_ t RTR 174-01

4.3.1 Proximity Amplification Factor (Hi/Hu)

An extensive wind tunnel test program was conducted from 1972-1981 at var-

ious facilities throughout the United States to provide a data base for Hi/Hu.

Table 11 is an example of Hi/Hu input data required for calculation of a disturbed

point. The matrix is for fl = -9 ° to 9 ° with c_ = -5 °, 0 ° and 5 °. Note that there are

two phases (1 and 2) of Hi/Hu definition. Phase I is divided into two parts, one

for the first stage launch configuration O/T/S and one for the second state launch

configuration (O/T). The flow in Phase I is fully turbulent for acreage points and

the values for Hi/Hu are generally provided by the wind tunnel data base. The

calculation requires the definitions of Hi/Hu for two Mach Numbers for both the

O/T/S and O/T configurations. A linear interpolation of the given Hi/Hu values

as a function of Moo in the log/log plane provides values of Hi/Hu at intermedi-

ate Mach Numbers. This interpolation is required for each c_, fl combination to

fill the main matrix at each intermediate Mach Number (time point). Figure 12

demonstrates how Hi/Hu is interpolated/extrapolated between and beyond the

given Mach Numbers for phase 1. In the calculation scheme the time that the

SPas separate is an input which triggers the transfer from the O/T/S data base

to the O/T data base.

Phase 2 is defined as that period of second stage flight when the flow is assumed

to be laminar and rarefied. A change in the Hi/Hu format occurs between phase

1 and phase 2. For phase 1, Hi/Hu is assumed to be a function of c_,/3 and Moo

whereas for phase 2, Hi/Hu is assumed to be only a function of Mach Number.

There was an insufficient data base for simulated second stage flight conditions to

define the effects of a and 3 on Ki/Hu so the approach was to envelope the existing

data at each Mach Number. This conservative assumption is not considered very

significant since the aeroheating environment during the phase 2 period of flight islow.

The switch from the phase 1 to the phase 2 Hi/Hu data base is defined as

the first time that the boundary layer is laminar in the undisturbed environment

solution. A smooth transition can be accomplished if the user applies the following

equation at the phase 1/phase 2 interface when preparing the phase 2 Hi/Hu database.

(B_r-----/_)laminar = ( IJ_//147\ .g_'U / turbulent

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i=_EM'I-EC _ RTR 174-01

4.3.2 Surface Roughness \H,mooth/'H, ou_h )

The foam which is sprayed on the ET leaves a rough textured and _ometimes

wavy surface which, for turbulent boundary layers, can significantly increase aero-

dynamic heating. Wind tunnel tests were conducted to quantify the amplificationof heating due to the roughness/waviness of the foam surface. The data was incor-

porated into existing empirical methods and surface roughness factors were derived

for design flight conditions. The details of the roughness/waviness tests and anal-

ysis are reported in References [7]-[9]. The surface roughness/waviness factors

(P_.F.) that are currently used in design environment calculations are as follows:

Nose cone (39.38 °) R.F.- 1.0 (SLA finish fairly smooth)Ogive R.F. = 1.3

Ogive Barrel R.F. = 1.1Intertank R.F. = 1.15

LH2 R.F. = 1.1

The roughness/waviness (I_.F.) factor is applied only for acreage points when

the boundary layer is turbulent.

4.3.3 Intertank Stringer/Waviness Factor (H,t_Ae,_k Hsmooth]

The intertank (852.8 < XT <_ 1123.15) cylindrical structure consists of eight

joined panels (two ribbed panels on each side and six panels with external stringers).

Figure 13 presents the intertank TPS design for the series of lightweight tanks

(LWT) 1-44. With the advent of the two gun spray equipment series of tanks >

LWT 44, the E.T. will return to an all CPR-488 TPS on the intertank and no

non-stringered external surface areas. Based on a study conducted by Engel [10]

that analyzed wind tunnel heat transfer data reported by Brandon [11] for wavy

walls, the following empirical relationships are recommended for minor and major

crossflow regions. These regions are defined in Figure 14.

Minor crossflow regions are defined as those where the flow disturbances due

to the presence of the Orbiter and SRBs are small and the crossflow angle ¢ is

less than _, 9 °. The equations recommended to calculate stringer factor effects on

average heating for minor crossflow regions are given below.

¢ - [asin_T - flcosST[

A = 1.2 +.01867

B = log A log Moo/.72428W.F. = l0 B

cross flow angle in deg.

11

I=_ I=- M-r" EE (_ !--.I RTR 174-01

where W.F. is the average heating amplification over a wavelength. Peak heating

areas near the cap of the stringers are not accounted for in the above correlation.

There are three major cross flow regions on the intertank. Each side of the in-

tertank has significant cross flow due to the presence of the SRBs and the top of the

tank experiences significant crossflow due to the presence of the orbiter. In these

highly disturbed regions, the cross flow angle can experience values from moderate

(<9 °) to _ 90 ° depending on the attitudes (_, fl) of the vehicle. Due to this reason,

it was decided to envelope the factors between 0 __ _ __ 90 ° which results in the

stringer/waviness factor for the major crossflow regions to only depend on Moo.

The following table for the strlnger/wavlness factor is recommended for the major

crossflow regions when the boundary layer is turbulent.

Moo Stringer/Waviness Factor

1 1.0

3 1.28

4 1.37

5.3 1.46

These values again only represent the average amplification of heating over a wave-

length. Later in the flight when the boundary layer becomes laminar and rarefied,

the stringer factor is assumed to be 1.0.

4.3.4 Hill ht

Tunnel Scale Factors (_)Flight/Wind

The Hi/Hu proximity factors discussed in Section 4.3.1 are normally based on

wind tunnel data measured on smM1 models of the full scale ET. There were six

instrumented flight ETs that were flown between April 12, 1981 and June 18, 1983

that measured aerodynamic heating and pressures at various surface locations.

The analysis of the flight data showed for certain locations and flight regions that

the wind tunnel and flight data did not agree. Flight test data from STS 1-3, 5, 6

and 7 consequently were used to generate scale factors between wind tunnel and

flight. The scale factor:

H i / Hu )flisht

was applied as a direct multiplier on the wind tunnel data at M=3.00 and 4.00,

Hi = (Hi/Hu)wind tunnel X f X HUo

12

F_EM-i-EC 1--4 RTR 174-01

to adjust the wind tunnel data level to that commensurate with flight measure-

ments.

A listing of the wind tunnel and flight test Hi/Hu data base as well as the

tunnel to flight scaling factors for each body point is on file at REMTECH, Inc.

13

i_ I_ M"F _ 0 i--I RTR 174-01

Section 5

ASCENT ENVIRONMENTS

5.1 Timewise Environments

Timewise ascent thermal design environments were generated at 367 acreage

body point locations on the External Tank. These environments are composed

of aerodynamic convective and plume convective heating. Environments: are com-

puted for lift off, first stage ascent, SRB staging and second stage ascent through

ET separation. SRM and SSME radiation heating are not accounted for. Envi-

ronments at body point locations for Xr < 1871 are composed of aerodynamic

convective heating only. For body points aft of XT >_ 1871, plume convection has

been included.

Due to the complex flow field interaction around the E.T. base region, several

ground rules were established to define the application of plume and aeroheating.

For the acreage locations, these are:

1. ET Aft Dome

(a) No aeroheating

(b) Plume convective heating throughout first stage

2. ET Aft Barrel Acreage (XT = 2000 to XT = 2058)

(a) Aeroheating from 0 to 95 seconds and throughout second stage

(b) Plume convective heating from 95 seconds to end of first stage

3. ET Aft Barrel Acreage (X T = 1871 to XT = 2000)

(a) Aeroheating from 0 to 95 seconds and throughout second stage

(b) More severe of either aeroheating or plume convective heating from 95

seconds to end of first stage

For those body points where plume heating was the main contributor between

95 and 126 seconds, design plume heating rates were generated versus time and

integrated along with the convective aeroheating component to give the total load.

14

RTR 174-01

An example of the timewise environments is presented in Table 12. This par-

ticular environment is for Body Point 7432 located at XT = 1132.2 in. and 0T =

315 °. Parameters listed include trajectory time, altitude (ALT), vehicle velocity

(vel) and Much number, angle of attack (ALP), angle of sideslip (BET), effective

angle of attack (AEFF), recovery enthalpy (HR), heat transfer coefficient (HCNV),

cold waU heating rate (QDOT), integrated heat load (QLoAD) and the Hi/Hu in-

terference heating factor (INTRF). Tabulated timewise environments similar to

those presented in Table 12 are on file at REMTECH, Inc. for each of the 367

body point locations.

5.2 Environment Presentation

Summary environments in the form of tabulated maximum cold wall heating

rates (Tw=460°R) and integrated heat load for each body point are presented in

Table 13. The maximum heating rates listed pertain to convective aeroheating

only. The loads include plume convection for body point locations XT > 1872.The Rockwell IVBC-3 environments are included for comparison purposes.

Most of the body points on the aft barrel section and aft dome are driven

by plume convection between 95 and 126 seconds. These points along with the

maximum aeroheating and plume convection heating rates are listed in Table 14.

The dominant heating component between 95 and 126 seconds is also identified. As

before, the Rockwell IVBC-3 maximum aeroheating rate is listed for comparison.

Timewise environments for each body point are presented in Volume II in the

form of cold wall heating rate versus time. Comparisons are made with the RI

IVBC-3 counterpart. Integrated heat loads are tabulated at the top of each plot.

These environments contain both aeroheating and plume convection. Compara-

tive comments are made giving the relative status of each environment from the

stand point of TPS impact. The environments are presented in numerical order

according to body point and are grouped according to component i.e., LO2 Tank,

Intertank, LH2 Tank, etc. Green spacer pages separate each group of body points.

In addition, the summary environments presented in Table 13 are also presented

in Volume II.

15

i=_ EM-r- _-C p-4 RTR 174-01

Section 6

REMTECH/ROCKWELL IVBC-3 ENVIRONMENTCOMPARISON

Of the 380 acreage body point locations on the E.T. for which environments

were calculated and comparisons made, 30 were not acceptable and required an in-

depth analysis. These are listed in Table 15. The remainder of body pointlocatlons

exhibited a favorable comparison between the REMTECH design environment

and the Rockwell IVBC-3 counterpart. The guidelines used to judge whether an

environment was comparable or unacceptable are:

1. Does the heating rate history track the IVBC-3 rate in the time frame 80 to

120 seconds when maximum heating occurs,

2. Does the maximum heating rate and integrated heat load compare between

the two, and if not, are the REMTECH values lower than the IVBC-3 values,

(heat load was considered secondary in importance) and lastly,

3. If the REMTECH environment is greater than the RI IVBC-3 environment,

does it impact the TPS.

6.1 40 ° Cone

The Rockwell environments for Body Points 70500, 70550, 70575, 70600, 70650,

and 70675 axe considerably lower than the REMTECH calculations. A summary

plot comparing the axial maximum cold wall heating rate distribution between

the two methods is presented in Figure 15. The wind tunnel data for this region

was laminar/transitional where as the flight data was transitional/turbulent. TheREMTECH environments included the nose spike interference effects that were

based on flight data. In addition, the REMTECH environments assumed that the

amplification factor over the entire 40 ° . cone surface was constant. The Rockwellenvironments were based on wind tunnel distributions that measured low heating

levels for XT < 350. The difference between Rockwell and REMTECH, however,

should not impact the current TPS design since the area is designed by the envi-

ronment at B. P. 70700 (XT = 354).

16

RTR 174-01

6.2 LO 2 Tank

The REMTECH design heating rates for Body Points 71363, 71369, 71381,

71388, and 71394 on the LO2 Tank do not track the Rockwell counterpart in the

time frame 80 to 110 seconds. The tLEMTECH maximum rate is higher by gener-

ally 1 Btu/fts-sec. In investigating this anomaly, it was found that the tLEMTECH

calculations were generally higher on the LO2 Tank from XT = 350 to approxi-

mately XT -- 600 at other body point locations also. This is shown in Figure 16

which is a comparison of the Rockwell and REMTECH maximum heating rates

on the foreward porton of the LO2 Tank. The reason for this discrepancy could

not be found. However, the TPS design is not impacted since the difference in

heating amounts to a difference in TPS of approximately 0.1 inches of CPR. This

is well within the uncertainty of 0.38 inches of TPS allowed during application.

TPS application tolerances are defined in Table 16.

6.3 Intertank

Table 15 lists the l.ntertank body points where discrepancies between Rockwell

and tLEMTECH existed i.e., the tLEMTECH environments were higher. At all

of these points the agreement is acceptable and the difference in heating in the80 - 130 second time frame results in approximately a difference of 0.1 inches

of CtLR being removed due to ablation. This is within the tolerance allowed

in applying the TPS (see Table 16). However, at Body Point 7355, which is

located at XT = 961 and 0T = 270 deg in the SRB foreword attach area (see

Fig. 4c), the difference in heating is significant enough to impact the TPS in thatarea. The current design in that area is a nonstringered configuration as shown in

Fig. 17a (Ref. 12). For this case which covers LWT 16-43, the configuration covers

the Rockwell design environment with a peak heating rate of 16.5 BTU/ft2sec.

The Rockwell environment is calculated for a non stringered configuration and

tLEMTECH agrees with this calculation as shown in Fig. 18. However, with the

advent of the two gun spay equipment series of tanks (LWT >_ 44), the E.T.

will return to all CPR-488 TPS on the intertank. With this configuration, Fig.

17b, there will be no non stringered external surface areas. In this light, when

the stringer factors are added to the heating calculation, tLEMTECH predicts a

peak rate of 21.8 BTU/ft2sec and the heating is considerably higher (Fig. 18)

than for the non'stringered configuration. The difference in heating results in

a difference of approximately 1.00 inch of CPR-488 removal. Consequently, the

design environment at B.P. 7355 needs to be recalculated by Rockwell with the

consideration of using stringer factors after LWT 43.

17

I=_ E M "T" E C I---I RTR 174-01

6.4 LH2 Tank

A lack of agreement between RI IVBC-3 and REMTECH was found at Body

Point locations 1401, 6582, 7694, 7931, and 7935 on the LH2 Tank.

Examining the environments in the vicinity of B.P. 1401, Figure 19, shows

that the IVBC-3 environment is high from a consistency standpoint within the

Rockwell set. In addition, the Hi/Hu data base was checked and the interference

factors listed for the IVBC-3 design environment are not consistent with the wind

tunnel data base (T/C 5252 FROM I_-97).

The Rockwell design environment for B.P. 6582 is believed to be high. This

body point is located underneath the LO2 Feedline at XT = 1127. Maximum

design heating rates at similar locations on the LH2 Tank are in the 1.0 to 3.0

Btu/fts-sec, whereas the environment for 6582 is 5.8. (See B.P.s 6590-6593, and

6603-6606). Examining the interference factor data base, the factors for B.P. 6582

range from 10 to 13 in the Mach 3.0 to 4.0 time frame. They should be in the 2

to 4 range.

Maximum heating rates in the vicinity of B.P. 7694 are presented in Figure 20.

The plot indicates that the REMTECH environment is too high. However, when

the Hi/H,, wind tunnel data base is examined, Figure 21, the Rockwell interference

factors appear low. The physical reason for the Hi/Hu data at this location being

high is not known, (T/C = 853 TFr-72) however, the heating level is low enough

that there is no TPS impact.

Rockwell environments for Body Points 7391 and 7395 are low with possible

TPS impact. A circumferential plot of maximum cold wall heating rate at approx-

imately XT = 2058 is presented in Figure 22. This plot shows the distribution of

environments in the vicinity of B.P.s 7931 and 7935. Body Point 7931 :_s located

immediately in front of the LH2 Feed Line. Heating would be expected to be high

due to the separation immediately upstream of a protuberance. The Hi/H_, data

base for this location was examined along with the interference factors tabulated

in the design environment. This is shown in Figure 23 for the Mach 3.0 and 4.00

results. Corresponding angles of attack and sideslip were obtained from the LWT

Trajectory and the interference factors from the REMTECH and Rockwell envi-

ronments plotted at these locations. The results show that the IVBC-3 data are

low. A similar investigation was carried out for B.P. 7935. The Hi/ttu versus

Beta data base (T/C 5051 Itt-97) is shown in Figure 24 along with the Rockwell

and REMTECH interference factors listed in the respective design environments.

The results show the Rockwell interference factor to be low at Mach 3.00, but in

agreement with the tLEMTECH factor at Mach 4.00.

18

i=_ E M"i- E C f-_ RTR 174-01

Section 7

CONCLUSIONS

Ascent thermal design environments were generated at 367 acreage body point

locations on the External Tank. These represented an independent set of calcula-

tions and served as a check on the Rockwell IVBC-3 set of design environments

used to design the ascent phase of flight. Direct one on one comparisons were made

between Rockwell and REMTECH. Of the 367 location investigated, 30 Were ques-

tionable requiring in depth analysis. Of these 30 only three represented a possible

TPS impact. These are B.P.s 7355 on the intertank and 7931, 7935 on the LIt2

Tank. At these locations, the Rockwell environments are considered low and need

to be revisited.

19

F_ E M"i- E C _--4 RTR 174-01

[1]

[2]

[3]

[4]

[5]

[6]

[7]

[8]

[9]

[lO]

[11]

[12]

References

Space Shuttle IVBC-3 Aerodynamic Heating Design Environments for the

External Tank Data Tape DN 2217, February 1988.

Crain, William K., and Nutt, Kenneth W., "NASA/Rockwell International

IH-97 Space Shuttle Heating Test," AEDC-TSR-82-V37, December 1982.

Engel, Carl D., and Praharaj, Sarat C., "MINIVER Upgrade for the AVID

System Volume 1 - LANMIN Users Manual," NASA CR 172212, August 1983.

Warmbrod, J.D., and Bancroft, S.A., "ETCHECK - Ascent Aerodynamic

Heating Computer Program for External Tank," REMTECH inc. RTR 032-

02, 1985.

Engel, C.D. and Praharaj, S.C., "External Tank Rarefied Aerothermodynam-

ics," REMTECH inc. RTR 022-1, January 1978.

Engel, C.D. and Praharaj, S.C., "ET Aerothermodynamics Study," REM-

TECH inc RPR 022-16, September 1977.

Engel, C.D. and Praharaj, S.C., "ET TPS Development Criterion and Flight

Instrumentation Program," REMTECH inc RPR 032-02, May 1978.

Engel, C.D., "External Tank Surface Roughness Heating," REMTECH inc

RTR 017-3, November 1977.

Praharaj, S.C., Engel, C.D., and Warmbrod, J.D.,

Methodology for the Space Shuttle External Tank,"

032-01, July 1981.

"Aeroheating DesignR.EMTECH inc RTR

Engel, C.D., "ET Intertank Stringer Interference Factor Methodology," REM-

TECH inc. RTN 032-1, January 1979.

Brandon, H. J. and Masek, R.V., "Measurement and Correlation of Aerody-

namic Heating to Surface Corrugation Stiffened Structures in Thick Turbulent

Boundary Layers," NASA CR-132503, September 1974.

"Space Shuttle External Tank LWT Thermal Data Book,"

80900200102, Revision C, March 1988.

MMC

2O

I=_ ==- M-r" _" C I.--I RTR 174-01

cq

e_i.-4

p_p-

p,.u-1

II

O

Oz

0J

i,...i

90 _

60

40b

20

0_

°

340_

320!

-- l-- I

, : i

: ! E

Ii I i

300i

270_

760.35)0i 1270.20!

25

i=_ l_-, M --F,.I=r. C i.,_I

rn

Ci-t

I'--

t'.-i..,3

II

C_

0t'-q

rno

C_v

270

240_

220

200:

180:

160 _

1401

120:

9oi

-"7305"7325_

'=306:

-7307

• -7309U-------o7329 o

[

iII

I

II

__.e. 6 13'ti_L__--6410_

i "

I [

I I

1I

• I

L I

[ I[ : ' I *

760.35 800_ 900!

Figm:e _.

L7365-Ii012

[

_ 7385--_7405 :7425 -

•/386----" 7406--'--7426

i -,.

• 7387

T

----------T [

359 _-_-o7369

I

7435'

T

[

I

7429_

1 "

i

i

______----.-q

I ; [

L

r------

F

I : , ' , "

T

i000

.nches)!

- 180 - 270 deg.

Continued

1i00 1200 1270.20

RTR 174-01

26

i_, _ M'll- _: C Iml

1002 •1007 •

1005 _

l/RTR 174-01

/' |

Body Point XT OTNumber

7355

1002

1007

1009

1005i011

961.22

965.22

970.22

970.22

971.22971.22

270.0

270.0

270.5

271.0

270.0271.6

Note: These points are not on the Bolt Catcher but on the

Intertank acreage beneath it.

c) Acreage Beneath Boltcatcher

Figure 4: Concluded

27

F_ EE M-I- E ¢_ I"1

U

II

tO

OZ

9O

60

40

2O

__5652s, °5628_-so_1.

.

O_

6489i

-_ II15 !

__ 74%0---7i70-- 74"80

3207432

_ 7442_7452L

300_

--0

- 7444_

J270

1124.5 1200_ 1270. Z

x,r ( IncUs)'

)308'_50309i311

" a) LH2 Tank Forward Section Acreage (O T -- 270 - 0 - 90)

Figure 5:LH2 Tank Acreage Body Point Locations

RTR 174-01

28

i=_ mE M-I-,_-- C i--I

I-I

r,_

i!

0

0Z

v v--7445--7455------7475---7485 ....

270

:7446

240

____: ___ •

47 ----7-457220

200

180

160

140_

__t

120!

901124.5 1200 1270.21

XT (Inches)

b) LH2 Tank Forward Section Acreage (O T = 270- 180-90 )

Figure 5: Continued

RTR 174-01

I

29

i=_E p,,/l-TEE C I--IIr'_c.

OJ

C

p-.

II

0

4o

A

r_

90

60

4O

20

0 •7520

340

320

I

i

300_

27011270.2_ 1300i_

n 595__i_i-

659o---- rt-6595- " 6593 I I 6594

7550

7551

w I

I

I 6

lT

, , i "I

1400_

i '

I

I:- i

I

c) LH2 T

RTR 174-01

i|l l

.,_ " Ill . n n _l

"%0_81150.809_

6603_6606• u

6699

--0 --v

7620 "" _ 7690Av

7760f

i

7691[ 7761

: r

i

j • ,

7692

-. 1

I ' : i

[

i ....

I

i -

Av

I 7694I

I

1500i 160G

XT (inches) t

akMid Section Acreage (ST = 90 - 0 - 270)

_igure 5: Continued

7762

I

L700

I I ' '

1800

14oir-----

1850.65_

SO

I=_ E M-II- E C I_1

-PI

p.p.

II

O

IJ0

Z

g3

_3

v

E-,13

270 e7525

240

220

200

180--e----7529

160

140

120

901270.21 1300

6

7555 7625 --

7556

7557,

7559 7629_

I

E q

i !

'I

I L

I i

, I

i ,

1400 15001

d) LH2 Tank Mid Section Acre,

Figure 5

: 7695

7696.

.7697 7767

0 ¸

7769

i

i ,

i

16001

XT (inches)l

e (OT = 270-180-9o)

Continued

i

1700! 1800 1850.65

RTR 174-01

31

i_ _-M -!- _- C F...i

9O

60

b

,J'l"

4O

uc-

.,4

t"

II

o('M

o

0

Z

340v

g-:

32O

5656s&s13og ,_51308 5i311 •

6633J-_ -" "_--'-6-________6_29_--6634..L -?

6637 _ _.,-_-6640-6639

----7830_--7850'

--__7831L i

Aq w

1414,

: 1, i

_7832--7__.852_-1409T

_----I" " _

663_

7920-- 7 c.o--o--

1300--1_

: "7921m7 c.m

I |

i L11

I

.l( It, .1i

_O

30309'

L704

--7834_

i(

2701850.65 19001 2000 2058:

(f_.hes)i

e) LHz Tank Aft Section Acreage (0 T 90 - 0 - 270)

Figure 5: Concluded

RTR 174-01

_2

I_ BE M -I" E C I'-'-I

Ol

..,.-I

r'-p..

p:

II

8O04

,J

oz

(n

}..i

v

270

240

220

20C

18C

ii

160

i

_oooIx_ Cinc,_s)l

1850.65 1900{ 20581

f) LHs Tank Aft Section Acreage (8 T = 2T0-180-90)

Figure 5: Continued

RTR 174-01

33 -¸

i=_ E f,,_"l- EE: C I--I

C

I- XT

#

Figure 6: Light

RTR 174-01

•C_Z PRESS. LINE

I.L

I

i

L02 FEEOLINE

sH_V 'V W WSH?

I I Iml • I i'r

1-13

'8,_o I_R I _ FR FR FR IFR, IFR _ IFR

' i;1- . -_,1 '- - - _ - - -

-- 1832.011

9=2.00

, TAN

_--c

8 _EO-_

8)R /'-" LJ_ F_-EOLINE

._LH@ RECIRCULATION

LINE

J_--Es_z-LH2 _ORTEX

I_.=.FLE

"Z-r400

,.:.,_ _o-'_ "x

_ -

XT L_348,-q0TAN

ight External Tank Assembly

34

F_ _" M'-r" _" C P.-_ RTR 174-01

(o_s/.r._) xJ.,zoo'i:_.A

0 0 0 0 00 0 0 0 00 0 0 0 0

T T--'-"_

0

0

0

0

0

0

t_0

F--4

>

,P'4

0

t_

t_

35

I_IE M -I-E C I---I RTR 174-01

400

3OO

v

eoio

<

200

i ' !

ET/ORBITER SEPARATION --:---':::----,r m

25

2O

15

I0

U

_Q

<',9IO

x

_J

I00

i 'i ,i _ ; ; .... tm

0100 200 300 4o0 500 600

TIME (SEC)

b) Second Stage Flight

Figure 7: Concluded

36

i=_ E M "T- EE C i-._ RTR 174-01

........ _....... t- -f_-_---- i .... "-_ i----t t--t ---'----_ ...... -t _-f--::Z---t-- --r .........

, _ F---- I-- , ' ' L +........... :-:- --::

-____

......................................... /, .............. :..--- • :.--_:.- ......

I

I .............. , .......... _, : :'_: :::::::::::::::::::::::::::::::::::::::::: : _-:. -- _

\\

¢:)_D

O

" " i I

/

L_ 0 L_ E)I "_

I

¢:)

a) Nominal and Dispersed Angles of Attack for First Stage Flight

Figure 8: Light Weight Tank Design Trajectory Angles of Attack and Yaw

3T

F:_"-:=:"r',,,,'l'r"_'(_ l--I RTR 174-01

O

0

"_'--_.- %.--+ .................. 1 _- ' _.. " ..... _--L_TLF-__T'_........ SF .......... L ...........

- --+ ...... ._':::5_:7. _ &q "- • .Z _,_ i{ _. _.LZ" , ........ t- "= ....... ' ..... O

_-'S7:_., _ ........ 1................. _ ................... 2'-_-22._--2- 2._5 :_ ", . 2...

.LL;_.5___ILLL-_L-:L_:LZL_-',_ .L .... _, :. ................... 7--S_?_?_.',L--_I.- .,_ . ;-

_7-_---_'-_-_"TZ ---."S.------ .....

_>..-. _..... ::.: .... :,-::: .--_., - -.: ....

:;_-r- ::.- _.-7.-: " : .: : -_-T;----_-:-_- . -: "--L_ " ' . "- 5-_ ..... " .' : _LZ_ L-i-S[-_..I--L±-ZL-_ L_ " " _ S ......

-":-:T--i-i--:::-_:_:T:-i__!:):--i__iTi:i_i-i::ii_i--::---_I ._L . - ....5----- " . ........ -_ " LLLZ_- 7_- ?55_ ......... _--?___-__-?---- -

0

0

0

0

I I

v

b) Nominal and Dispersed Angles of Yaw for First Stage Flight

Figure 8: Continued

38

I_ _: M"T" IZ: C I--,I RTR 174-.01:

5

0

v

-5

0

-10

-15

-2O

• :: : , , .

I00 200 300 400 500 600

TIME (SEC)

c) Nominal and Dispersed Angles of Attack for Second Stage Flight

7OO

Figure 8: Continued

39

i=t ==" M-r ==" _ I--i RTR 174-01J

o

10

-5

-10

-15

-2O

I00

TIME (SEC)

d) Nominal and Dispersed Angles of Yaw for Second Stage Flight

i

700

Figure 8: Concluded

4O

I=_ EEM -I- E C I--I RTR 174-01

........ ; .... ;-- Oi i I ' ' _ ..... ,::;

I

' i

T

C)__o •

-I

========================....... .'F:_:. _-_':.::TT:..7:.:.-.___:......:_:::"-':._.:7::

I-,-I

(_ cO r_ _ _

(6ap) e _/Suv aA_M _0oqs

,/1

8

0

0Ip.,i

0

r../'j

00

_0i e,,_l

F_EMTEC _"4

600

500 1

N+_ 400 ':

,,_ . !.,

_ ;!i!i!i300 _:i::::

200 ----i i.,i.:::liT::

,.j,A.

i_:!iii!I00 _,.;:,.,

!:!I!T!:

r:!!::o--:: .-

i::!L_I

0300

I

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

':M ;,'." :%:

i;iil;[i "!i!i i:: !iii

?!!!i_!i!!iii:ii i!i:

.::;:, '+rl:

........ ::A ?I!:

'h_ "E:li'ii¥i !'::r

:_,_i!'i)iliiii,_:,

L':.=.iF.:L!iS_i!-_..

;;.: HH i:;Ii: _!i; :;[! £ET!

!i ;;iiii....!i i! _:::

=;:: ii!Eii!}i:::! .... I:H ....

: !; :;:: i:!! ,q;;:

::L. '(ii .,r

m: ...... FITT:iiii!!:!If_!:;

.A:'il;:'Iiiili•" :H; ,,,,

,, ::I; T!I!

i:?iI!_.i!'_':!!!

!i;: i!ii ......::;!!: lili ;H!

iiil:l....

:-2. --'_ -4-=

:iii21!ii! _L[ !!ii

: _i:ili!Ti i!:I

: ; %"I, ....

i:i! i!i!

.... i;::II::: :!1:

L;_ :If:

ii!ili!ii l:'_: ::l:

:_I!1.'_!i!i;t

_::::::ii

iit.-.':-!_:5 :iki!

!i!I,.:,!ii!_.

/:_ ..... li

it-i-hTi:!i ::rI_I

:m iT'.!}H!II!i!ili!

_ !If;

:" ii_iliiI:ilii !_ri

1 i m:

!I !ii i!ii_.r:: ii_i i?! !iii

,_, _ ill !iii

I_ { il i :: i!ii'

;:74_:_:l t'_ ::v. i}}!

a_:..:i,:"=i,I,_-..ilil ii_iT' '!"1::'" : t"

;::: ii!ilii!i .... tLfi

!! :::v::::r ',}}I

i000

XT

i!i!:!Li!i_ilifl=_,;,_::t,,,. ,:,,,.::

_E_;:i.,,!i i_ . ...,....

::I":_!L'I:::: I !1_1!_

TRAJECTORY CONDITION

RTR 174-01

;-iiii!4j!ili::: :::!_ir :::

:"! : i_1-.]

:": :;.,I- ..

!:/QE! :-)

.i!i:=T _

L_li_i!Ci!

:::: ;:,,v,,

:-_.":.-,:i!i!!!Y!_ii I:iil_

::": !L _.

:!:Ti-;

• M_=3

• A1t=74,541 ft

• V.=2900 ft/sec ^

• F. =2821 Ibf/ft._

• P= '=1630 Ibf/ft _

-... _--or .....

I!:i! ........ :::;[:i;v_:iiii!ilihu:lt:::h:::h:: h!:: ii!i:;]:

• I!i ' =!iii i!iil':_!ll-iiii! .....'==;'4

'M: 1;:: .... "" [:: I:t:!!'[:i:Tl',:.:l::- ;::I I I

1500500 200

v

200

100

03OO

;l

I, "----. I:1. _ ' • . , L : ...... -4 ' ' ....... ';;-I_'L_z----I---L " , _ . ,,'i_-,-':- "::-I:-:- 7':':'i'-7- ' :-':,.'_:':T--_:---:_'--TT---: "-,; .. - :;;; :: : .., :. ; ................. ,, ; ....... !. L "" ' ............................ : : : ';:: ;, ::: ........ I ....... I, . ; • . :::l:r::r_:::._:tI_ )r'.v: ,:: ;: ::: :::; .::,. :::: :_:'. :: ::-': :'::I;:: :::-I.::: ;.:,_ ...... _....

TRAJECTORY CONDITION |:}i il}:;

............... :....... : =:..': ....::" === .:.:= ._ :: .Alt=109,863 ft -_: l--_-_:.__-: _-..... :;::=_ ': _ "_ _ ....... i""-",= • V=-4293 ft./sac :.-: .::,....

:":_:' :±L: .::L !:._ ;"_ ::' '"! :-; _ :--" ';;I_;_;:;...L._ _ '" :'; _'C - I-;-;L;-L"I I_I ; ........ 1 I

........................... i .... I '

...., .......................... '*......__ ............._'_, .............t,=::': ::I._,:::t:.:_::,:::,

:_ ___. _.._ :.::__..:- ._ ...... _----.--- - ---:-:- .-- --:-- --.-:- - ..... , ---

500 I000 1500 2000

XT

Figure 10: Surface Pressure Distribution on the ET at M = 3.0 and 4.1 for the

LWT Design Trajectory 42

i_ E M -,,11-E_II:C i,,,.,11

o

,-.i

!

.....tI0Q

°0

)Q

Q

0

,.t..;

o_,,4

o0

t

_-4_ i

l_'M-r" _" C I---I RTR 174-01

hi

hu

4

2

13

O/T CONFIGURATIONlu

_J

L

II i I I ,

4 5 6 7 8

M.

B. Pt. 7420

c_ = -5"

B = -9"

(9 Input Data

hi

hu

51

3

2r

1

I

O/T/S CONFIGURATION

I i I

2 3 4 5M_

Figure 12: Example of Interpolation/Extrapolation of Hi/Hu for Phase I

44

F:_EM'T'_ C m--4 RTR 174-01

!

+Z AXIS ]

BX-280 FOAM.

FLUSH TO TOP OF

STRINGERS

Innn-

ORBITER SHOCK

_. IMPINGEMENT ZOHE(ISLAND 17)

101R-1100- LI i04,5

1121- _I117,5

I

1+Z

CPR U8

tIIGH HEAT ZONE. CREATEDBY_

DISTURBED FLOW FROH I/T \

AND ORBITER

SKIN & STRINGER PANELS (÷Z & -Z)--_LY UNDISTURBED FLOW

THRUST PANELS (÷Y & -Y)CREATED BY DISTURBED FLOW

FROM THE SRBs,

÷Y

_;;._,-'

tSKIN

CPR 488

BX250 FOAM

FLUSH TO TOP

OF RIBS

Figttre 13: Intertank TPS Design mad Surface Finish Details

45

I=_ ==" I'vl "1- E:: C I--I RTR 174-01

o

8

A

r_

O*_.,4

O

r_O

c_

O

O

O

r._

O

c_

I--I

4G

F:__" M "r r._._._.="C t---! RTR 174-01

O

4'r

371.0

• - ,,

SYM 0T B. Pt. ID

0 0 70XO0

[] 180 70X50

270 70X75

O. 14 60111

O 8 60112

--- RI i

-- REMTECH _,

RTR 174-0I

25

15

............. 7---------'. .............. _ -- ...... !

i0340 350 360

Figure 15: Comparison of Maximum Heating Rates for Acreage Points on the40 ° Cone

48

!_ EM7 E C I'-'1 RTR 174-01

,i

,4

q4

_r,.}

,i,,q,q

:P'

d

10

Eli

s -i_i

t-_-s

EE

4 _'

'_0 _ ,

SYM e T (deg) BodyPoint

C) 315

• o• i

Source

70188 71388

71000 71300 71500 71600

70188- • RI IVBC-3

71788 REMTECH

7100 -- ," RI IVBC.3

71800 REMTECH

BODYPOINTNUMBER

718OO

a) A_ial Distribution

Figure 16:L02 Tank Acreage Heating Environments (350 _< XT S 600)

49

I=_ E M"I- mE C I"-I RTR 174-01

b) Circumferential Distribution

Figure 16 Concluded

50

I_ I_ M T I::" C I--.I RTR 174-01

850 -

900 -

950

1000Z0

1050

_ ' THRUST PANEL _

I • Z ZBP 7305 _

• 7355

/ eP7o6s I \ZONE 3 • ZONE 3

1100 - BP 7405

1150 I I I t I = t I I ,,_ I220 230 240 250 260 270 280 290 300 310 320140 130 I20 110 tO0 90 80 70 60 50 40

THETA (DEGREES)

CPR-488 BX-250 FLUSH

.55" MIN TO TOP OF RIBS

,- .

.08"-.81 • .055"o 1,05"

ZONE 1 (Z-Z)

* Source: Re£ 12

.08"

MIN

!

t

STRINGER PANEL I1,.

II

ZONE 4 [

x x I ] • LI so63o1

BP740; I W W ZONE2 1

[ ' BP7430_"÷..._ II , I I I I | I I

330 340 "350 0 10 20 30 40

THETA (DEGREES)

CPR-4B8 BX-250 FLUSH

0.90_ S_RINGERS

I L 0.08" MIN

ZONE 3 (Y-Y) : A = 0.5" MIN, B = 0.25" MAX

ZONE 4 (X-X): A = 0.3" MIN, B = 0.5" MAX

ZONE 2 (W-W)

a) LWT 16 - 43

Figure 17: Intertank TPS Configuration

51

i_ l_- M -i.,-, _,. _ I..-I RTR 174-01t

CPR-488

._Z

ZONE

A

B

C

D

ESTRINGER PANEL

CPR THICKNESS

0.75

0.50

0.30

0.40

0.90

___ CPR-488

ZONE CPR THICKNESS

A 0.75.

B 0.50

C 0.30* Source: 1gel. 12

THRUST PANEL

b) Intertank Minimum TPS Requirement Assuming Uniform Spray (44 & Up)

Figure 17 Concluded

52

I=_ I=" h,,,'l'l- E C H RTR 174-01

_t£V_I DMI£VHH "I'IV_A (NOD NDISX(I

Figure 18: Intertank Design Environments for B.P. 7355

53i

i:::_ E M .-1,,-i_- C i._ 4

3.0

_ 2.o

0

RTR 174-01

' / i

NNINNNN '___ i= XT[ !

1600 1700 1800 1900 2000

XT (inches)

a) Axial Distribution

O RI IVBC-3 I

[] ..REMTECH I

3.0

2.0

1822

0280 300 320 340 360

e (deg)T

b) Circumferential Distribution

Figure 19:LH2 Tank Acreage Heating Environments in the Vicinity of B.P. 1401

I

54

I:_ I_" M'T" Ii_ C I-..4RTR 174-01

3.O

SYM SOURCE

O RIIVBC-3[-] REMTECH

2.o

01300

........ !:---:: +?:i;:--; :-::L: +: "

---+ :.... _'-: J . I ..... '_ ....... ; ....... I ,

1400 1500 1600 1700 1800

X T (inches)

a) Axial Distribution ,i1

3,0

2.0

1.0

0 L

2601 I I , i I, " : ,I

280 300 320 340 360

O (deg)T

b) Circumferential Distribution

Figure 20: Maximum Heating Rates in the Vicinity of B.P. 7694KK _

I_ _;; M-r" _ _ I.--Ii

II II II

Figure 21: Hi/Hu Data Base for B.P. 7694

56,

|

!

I

i::_ W_-M .-.r E C l,--I

.... ; ....... _..... !.... !:"_+ -_" t-r ---_.--_C_ ! i, IT---T_ ,--F-- ,

-- : - LT-.: :_LT;TCL_, ;T',::LL'_L__._E,-EL-EL ..... _.._ i +_ '--'- ' -- _ ....... l ....

Y

......... k ..... 4 ............ T ..... T-- _--"#'---_"*r ...... i--+T -- ,

-1 :TFL:T _ ....... _ [ 7_L.-

-- t ......

ill

RTR 174-01

1

¢_

r,,¢,,III II II

-- - .._- ilL.__i

........ ..ii,

........ : ....... TT+_----E:-F _'._:ET_I --LL:T+:- "

_:__lL: .'T" " -:LC+ET:-,IE7 .... - ..........

l'-;:. ;_ --',TT ,

..... ._L-" ".-T_L-[--LLcL-+--: r -_ . +/ _ _i : : : _ _

b) M = 4.00

Figure 21 Concluded I

.57_

I=_ E¢ M'I" E¢_: I---I RTR 174-01

RTR 174-01

@,L

MP

a) M = 3.00

Figure 23: Hi/Hu Data Comparison for B.P. 7931 i

_9

I:::_n_"M '-I-_" C I,,-4 RTR 174-01

,i

i RTR 174-01

.r

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

....... :.... i ................... a) M = 3.00

Figure 24: Hi/Hu Data Comparison for B.P. 7935

61 ¸

I

i::_ E: M-I" I_ 0 I"-IRTR 174-01

[]

("4

Z

b)_ : _.oo

- II

,I

................... i .......

Figure 24 Concluded

62

o_

t_

I

F_ _-_,,1 -T- x=-_ _--_ RTR 174-01

Table I: 10°/30 ° Nose Spike and 40 ° Nose Cone Body Point Locations

BODY PT

60133

60101

60122

70300

70350

70375

70400

70450

70475

60130

70500

70550

70575

70600

70650

70675

60111

70700

70750

70775

60112

70800

70850

70875

COORDINATES

XT OT

(in) (deg)327.66 0.0

328.00 0.0

328.00 180.0

329.00 0.0

329.00 180.0

329.00 270.0

335.00 0.0

335.00 180.0

335.00 270.0

338.00 0.0

342.24 0.0

342.24 180.0

342.24 270.0

345.50 0.0

345.50 180.0

345.50 270.0

349.00 14.0

354.50 0.0

354.50 180.0

354.50 270.0

357.00 8.0

364.50 0.0

364.50 180.0

364.50 270.0

LOCATION

30 ° Conical Nose Tip

10 ° Nose Cone

40 ° Cone

63

I=_ E I_/I -!" E C I---I RTR 174-01

Table 2:L02 Tank Body Point Locations

BODY PT

70900

70950

70956

70963

70969

70975

70981

70988

70994

60400

60405

60407

60409

60411

60413

60418

60500

60507

60509

60510

60517

71000

71050

71056

71063

71069

71O75

71081

71088

71094

60601

60607

60609

COORDINATES

XT

(in)375.10

375.10

375.10

375.10

375.10

375.10

375.10

375.10

375.10

402.50

402.50

402.50

402.50

402.50

402.50

402.50

409.90

409.90

409.90

409.90

409.90

421.30

421.30

421.30

421.30

421.30

421.30

421.30

421.30

421.30

422.30

422.30

422.30

8T

(deg)0.0

180.0

202.5

225.0

247.5

270.0

292.5

315.0

337.5

357.4

16.9

24.3

31.5

38.7

46.1

65.6

0.1

24.9

31.5

38.1

62.9

0.0

180.0

202.5

225.0

247.5

270.0

292.5

315.0

337.5

3.2

25.8

31.5

LOCATION

LOs Tank Acreage

64

!_ 1_ M'T i_ C I'"1 RTR 174-01

Table 2 Cont: L02 Tank Body Point Locations

BODY PT

60610

60617

60701

60707

60709

60711

60716

60802

60806

60807

60809

60810

60816

71100

71150

71175

71200

71250

71263

71275

71288

60907

60909

60911

60915

61009

61109

71300

71350

71356

71363

71369

71375

COORDINATES

XT @T

(in) (deg)

422.30 37.2

422.30 59.8

432.10 5.0

432.10 23.7

432.10 31.5

432.10 39.4

432.10 58.0

437.60 5.9

437.60 21.5

437.60 26.5

437.60 31.5

437.60 36.5

437.60 57.1

453.60 0.0

453.60 180.0

467.40 270.0

467.40 0.0

467.40 180.0

467.40 225.0

467.40 270.0

467.40 315.0

474.20 23.7

474.20 31.5

474.20 39.3

474.20 53.5

512.10 31.5

512.60 31.5

513.60 0.0

513.60 180.0

513.60 202.5

513.60 225.0

513.60 247.5

513.60 270.0

LOCATION

L02 Tank Acreage

65

I=_ E !_/1 "T" E C F--! RTR 174-01

Table 2 Cont: L02 Tank Body Point Locations

BODY PT

71381

71388

71394

61111

61114

61209

71400

71450

71456

71463

71469

71475

71481

71488

71494

61309

61311

61313

61409

71500

71550

71556

71563

71569

71575

71581

71588

71594

61509

71600

71650

71675

COORDINATES

XT 8T

(in) (deg)513.60 292.5

513.60 315.0

513.60 337.5

551.30 37.3

551.30 49.0

591.40 31.5

606.00 0.0

606.00 180.0

606.00 202.5

606.00 225.0

606.00 247.5

606.00 270.0

606.00 292.5

606.00 315.0

606.00 337.5

632.30 31.5

632.30 36.4

632.30 46.3

673.90 31.5

698.00 0.0

698.00 180.0

698.00 202.5

698.00 225.0

698.00 247.5

698.00 270.0

698.00 292.5

698.00 315.0

698.00 337.5

715.80 31.5

751.50 0.0

751.50 180.0

751.50 270.0

LOCATION

LO2TankAcreage

66

I=_EM-T- EC l_l RTR 174-01

Table 2 Cont: L02 Tank Body Point Locations

BODY PT

61609

61610

61611

61613

61709

61809

61909

62009

71700

71750

71756

71763

71769

71775

71781

71788

71794

62109

71800

71850

71875

COORDINATES

XT OT

(in) (aeg)759.20 31.5

759.20 33.8

759.20 36.0

759.20 45.1

762.20 31.5

773.70 31.5

786.20 31.5

793.10 31.5

796.50 0.0

796.50 180.0

796.50 202.5

796.50 225.0

796.50 247.5

796.50 270.0

796.50 292.5

796.50 315.0

796.50 337.5

827.10 31.5

841.50 0.0

841.50 180.0

841.50 270.0

LOCATION

LO2 Tank Acreage

67

I:=_".="r',_ -r" "_" C I---_ RTR 174-01

TABLE 3: INTERTANK BODY POINT LOCATIONS

BODY PT

7300

7309

7307

7305

7304

7302

7301

7306

6410

6413

6394

7320

7329

7325

7324

7355

1002

1007

1009

1005

1011

7350

7359

7354

7352

6301

1012

7365

7360

6368

6369

6367

7369

COORDINATES

XT 8T

(in) (deg)

884.85 0.0

884.85 180.0

884.85 225.0

884.85 270.0

884.85 292.5

884.85 315.0

884.85 337.5

884.86 247.5

890.00 141.3

900.00 142.6

905.00 31.5

929.14 0.0

929.14 180.0

929.14 270.0

929.14 292.5

961.22 270.0

965.22 270.0

970.22 270.5

970.22 271.0

970.22 270.0

971.22 271.6

973.43 0.0

973.43 180.0

973.43 292.5

973.43 315.0

983.46 23.5

991.07 270.0

994.40 270.0

1006.65 0.0

1006.65 15.0

1006.65 19.0

1006.65 29.0

1006.65 180.0

LOCATION

Intertank Acreage

68

/=e i_-/_A .-.j- ==...c p....l RTR 174-01

Table 3 Cont: Intertank Body Point Locations

BODY PT

7364

1746

1738

7387

7386

6331

7380

7385

7381

7400

6408

6409

6407

7409

7406

7405

7404

7401

6395

56282

7420

6429

6427

6424

7429

7427

7426

7425

7424

7422

7421

6286

1100

COORDINATES

XT @T

(in) (deg)

1006.65 292.51021.70 13.5

1021.70 29.3

1025.80 225.0

1025.80 247.5

1026.00 16.5

1038.03 0.0

1038.03 270.0

1038.03 337.5

1069.40 0.0

1069.40 15.0

1069.40 19.0

1069.40 29.0

1069.40 180.0

1069.40 247.5

1069.40 270.0

1069.40 292.5

1069.40 337.5

1074.40 36.0

1080.05 32.5

1102.62 0.0

1102.62 19.0

1102.62 29.0

1102.62 37.7

1102.62 180.0

1102.62 225.0

1102.62 247.5

1102.62 270.0

1102.62 292.5

1102.62 315.0

1102.62 337.5

1111.20 23.5

1111.85 343.0

LOCATION

In_ertank Acreage

69

i_ !_ M"f" !_ C I--'1 RTR 174-01

Table 3 Conc: I.atertank body Point Locations

BODY PT

1107

110I

1108

7430

7439

7437

7436

7435

7434

7432

7431

COORDINATES

XT

(in)1111.85

1121.08

1121.08

1123.15

1123.15

1123.15

1123.15

1123.15

1123.15

1123.15

1123.15

_T

(deg)348.0

343.0

348.0

0.0

180.0

225.0

247.5

270.0

292.5

315.0

337.5

LOCATION

Intertank Acreage

70

I=_ EE M "-r"E C I---! RTR 174-01

Table 4:LH2 Tank Body Point Locations

BODY PT

56283

6582

7440

7449

7447

7446

7445

7444

7442

7441

1115

1122

1105

1110

56505

50108

50109

50111

7450

7459

7457

7455

7452

7451

7470

7475

56575

7479

7480

6489

7489

748556525

50308

COORDINATES

XT 8T

(in) (deg)

1124.50 32.5

1127.56 23.5

1137.29 0.0

1137.29 180.0

1137.29 225.0

1137.29 247.5

1137.29 270.0

1137.29 292.5

1137.29 315.0

1137.29 337.5

1139.53 12.0

1139.53 17.0

1139.53 343.0

1139.53 348.0

1149.99 32.5

1151.80 30.9

1151.80 30.9

1151.80 30.9

1167.21 0.0

1167.21 180.0

1167.21 225.0

1167.21 270.0

1167.21 315.0

1167.21 337.5

1201.51 0.0

1201.51 270.0

1204.74 32.5

1209.51 180.0

1229.96 0.0

1229.96 19.0

1229.96 180.0

1229.96 260.0

1269.24 32.5

1270.20 30.9

LOCATION

LH2 Tank Acreage

71

I_ IE M TIE C I-'1 RTR 174-01

Table 4 Cont: LH2 Tank Body Point Locations

BODY PT

50309

50311

7520

7529

7525

6587

6588

7550

6555

7559

7557

7556

7555

7554

7552

7551

6589

6590

6593

6594

6595

6596

50508

50509

50511

6597

7620

7629

7625

56534

5080850809

50811

COORDINATES

XT 8T

(in) (deg)

1270.20 30.9

1270.20 30.9

1297.83 0.0

1297.83 180.0

1297.83 270.0

1334.37 23.5

1358.90 23.5

1359.15 0.0

1359.15 40.0

1359.15 180.0

1359.15 225.0

1359.15 247.5

1359.15 270.0

1359.15 292.5

1359.15 315.0

1359.15 337.5

1366.38 23.5

1371.99 23.5

1375.26 23.5

1380.41 23.5

1383.91 23.5

1387.65 23.5

1399.40 30.9

1399.40 30.9

1399.40 30.9

1401.00 23.5

1486.49 0.0

1486.49 180.0

1486.49 270.0

1591.74 32.5

1593.20 30.9

1593.20 30.9

1593.20 30.9

LOCATION

LH2 Tank Acreage

72

i=_ E M "lr" E 0 l--I RTR 174-01

Table 4 Cont: LH2 Tank Body Point Locations

COORDINATESBODY PT

56535

7690

6699

7699

7697

7696

7695

7694

7692

7691

6603

6606

776O

7769

7767

7766

7764

7762

7761

1401

6614

1404

6617

7830

7839

7837

7836

7835

7834

7832

7831

7850

7859

7855

iT

1597.19

1615.67

1615.67

1615.67

1615.67

1615.67

1615.67

1615.67

1615.67

1615.67

1618.69

1621.96

1743.02

1743.02

1743.02

1743.02

1743.02

1743.02

1743.02

1822.38

1865.39

1868.51

1868.66

1872.20

1872.20

1872.20

1872.20

1872.20

1872.20

1872.20

1872.20

1898.04

1898.04

1898.04

OT

(deg)

32.5

0.0

19.0

180.0

225.0

247.5

270.0

292.5

315.0

337.5

23.5

23.5

0.0

180.0

225.0

247.5

292.5

315.0

337.5

309.4

23.5

309.4

23.5

0.0

180.0

225.0

247.5

270.0

292.5

315.0

337.5

0.0

180.0

270.0

LOCATION

LH2 Tank Acreage

73

I=_EMTEC F-_ RTR 174-01

Table 4 Cont: LH2 Tank Body Point Locations

BODY PT

7852

56565

1406

1409

51308

51309

51311

1414

6632

6633

6634

6637

6638

56575

6639

6640

6909

51608

51609

51611

1021

1300

6647

6929

7920

7929

7925

7922

7921

1041

1023

1043

1025

1205

1303

COORDINATES

XT 8T

(in) (deg)

1898.04 315.01914.24 32.5

1914.65 304.0

1914.65 315.0

1916.00 30.9

1916.00 30.9

1916.00 30.9

1936.79 330.2

1955.30 23.5

1962.78 23.5

1968.39 23.5

1971.66 23.5

1976.81 23.5

1978.74 32.5

1980.31 23.5

1984.05 23.5

1999.54 19.0

2028.00 30.9

2028.00 30.9

2028.00 30.9

2031.65 289.5

2032.00 355.0

2033.00 23.5

2036.45 19.0

2036.46 0.0

2036.46 180.0

2036.46 270.0

2036.46 315.0

2036.46 337.5

2040.75 250.5

2048.45 289.5

2048.75 250.5

2052.65 289.5

2053.50 312.6

2053.50 355.0

LOCATION

LH2 Tank Acreage

74

!=_ I==-r,vl'l- IE: C I--.I RTR 174-01

Table 4 Conc: LH2 Tank Body Point Locations

BODY PT

1046

7930

7939

7937

1054

7935

1032

1211

7931

1307

1309

1704

1047

1705

1206

1305

1026

1306

1207

1049

1028

1050

1712

1713

1715

1716

COORDINATES

XT

(in)

2053.75

2058.00

2058.00

2058.00

2058.00

2058.00

2058.00

2058.00

2058.00

2058.00

2058.00

2058.00

2063.25

2063.60

2064.00

2064.50

2065.45

2067.50

2072.00

2075.25

2075.95

2083.25

2084.40

2084.40

2084.40

2084.40

8T

(deg)

250.0

0.0

180.0

255.0

247.0

270.0

283.9

319.4

337.5

357.1

358.8

340.0

250.5

340.0

312.6

355.0

289.5

355.0

312.6

250.5

289.5

250.5

343.8

344.5

346.3

350.5

LOCATION

LH2 Tank Acreage

75

F_ l_: I',_-I- E:: _ I--'1 RTR 174-01

_1' O. e" 4o • • • O* • , • OI q_ • •

0 mO.O0010 0 i 00_0 0 0,000.00 _,_ _ _ _._ ,-_ _ ,-, _ ,-,

'_ .__ _ .o .,. • ._-:..:..:_-:_ _.N _ _.• _._ _.._O0000.O00_O00, O00-'_**_q'-'_O. O00000. O00000 O0

._ _) • Os • ql_ • • it iN • • e! 4) ql ll* • • ill II" • •

I _ _00_.O O;O00_O00. O00,,"*-,_0,,=*,.*_'O0_-OCPO000"O0000

0,0 0.0 _ _;¢'_ N e_ e,,dU

/"_. _1

_ ...,..,........,.:.-: _._-: _.,_.4 Ik • • @ • • I)- • •

ooo oooo,oooo o oo oooooI I '1 t I I I: I I I.| _ I , I_i.l:_W I. ' I I , * I | i I * I i ' i I _joooo_ooooooo_o,,oo o.o o.o o._oo.o_ooo,,__,_ _ _

.41",..*

, -- _ = _ _'_ O--_" =-- _'_ ' _--O_-- _ =-- _ _ " _ " _ _ _ 1 __ _

q.) "_ _,* I t I i -I I I. I t I i E I i ' i I I I I I . I I I I | i I | I i i I I I

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'7'6

F=__ r',_-r'_: C _--.I RTR 174-.01

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! • . ,

Noo_." _..-._ o. o. o.lo. N,A _ o,,i.o o. N N _ r, N N N,,4 N,..._ O,_ _ 0",_,-. _o_ _ F-..-1• • e_ Q i • • e • • I_ • • • • • • • • • • _ • • • • o _1 e • _ • • _ (lOe • * • •

oom,,.o_ _N..O,CP" O_m,O=qC_..-*N,O0,_ ,OOPL_OO_¢OP - 0"©¢0_',_

oo, oo ,-,,-,_----,-1NN,-*,-.-' --o ooc oo_o,-, oo oo ooooo

"" '' "'''''''''" "''''' '-_;_; o

...-.-----.-----.-----. oooooc_oooo-b_ooOooQO000C_O 0000 C_O0000C_O0_OOC O0000_O0000GI O0 O00I

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• • • eq • • • • • • • • • • • • • • m _ O_O0_,,_t,_ e • • •_ o_ ,,,__,_,_.4o,_=,=_._,.,_-=_ _:_:::;_ ®,,,,-,,,,A"" " " "_" " ' " " "" ' ' '' " ' ' " " " "" " " '" " "

,_ _ _ _ .4..,11 _ _ ._ r'- P.- P-f P. _ =0 _ =o =1 =c _o = =0 =0 ¢ t,. p..0 .o _ =.t .t .¢ _ _ _ _ _ ,-, o o.o, _-t

.,I" .¢ _ <1".,11

_<.' ,,_,._.,_,_,,_ _,,oo_o_o,,_,,_......... ,_,_,__, ,_-__. _ ___-oo , _ oo, , ? ? ,_oo o o o oo o o o ? _? ? ? ? ? _ .,.,°o =.oo_,,, ,_ .,_,°°°°_,,,I_ w_,,,_u_uuJUJu_,,.q_u_uuJ_Uwu4,.u_Jww_u_ u_'w_uJ_u_J_u_uuJ ,,,_',,,.,,.q

ooooo_o ocI'ooQoO¢Iooc1oooooc oooooc:lOOOOOC_oooo c_

• @ • e i_, • • • • • • • g e, • e • • 0 • • • • 4 4 • • • • 4 • _) • • •

N."w'l"_ r'l "_',_,-,'_r.-P.. r,-,'-_P...0 ._1.0 .o C_O O _ _'0 , , , , ,

-_ t ,.I I I , I'I I I I I I I , , , I , ..w.._.._lI I T';' I , ',=l I i

_"i '" ° °' _=.=°'°'="_

-oo.=_.-,,-,_o.o._oe..'_l.o.o"-_-,--o'to_ .... ,_"_ . .. , • . o . o . • o • o., ,.

"",1 '"'"""1",, "' '"",,,,,,,,,""',,.,_ "''" • .....,.....,..... ..... ,

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

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_.__._._joooo. _,ooooo_o0oooo_._._._._._.o_. __oooo.,-1_ooo_._ooao o Q o .....

7'7

F=_=" M"r" _: C P--4 RTR 174-01

I!

q

' j1

??_???o_000

eo_ee_

IIiil

i.

_OOq

.iOlill

O_mN_

,_ON_

NNNNN_ NNNNNN

N N i I'M ¢MNff'- I"-NN ,-_ ,-q 0 0 0

,0 ,0 ,01 ,0 ,0 ,¢

gc;dgg_

I

,:;go, c;o="'I

??_?o?t.l,.I UU t.l.II U,.,I t.l.,I 1.4.1

o, 00_ m ,0 ,_

mm_mm_

!

" i

i

I

dgd.gg_i

??_???

??_??_ ? ? ,_?.? _'? ? _i?':i"T ? ?o.? ? o_,_,,, = ,,,= = =,,,ooo o_ ,,.'-=C O _) t.t-lw u.lu- uJ

_._.._ oo ooo_o___.. o._ _....,. •N ."q _ ,._ _ _ _" ,_ "_ _ ,,l" ,,_' _ "_ -'_ ._ N _ ''' "_

• • 0 • • • e_ oP_O 4 • •

_'1 -,_,o = J't _", ,,le" -:'1 '¢ "_" =3

, = ,, , , i , , , , ,,TTi

. . • ....._.._._..w._ ,w.w.-_-_.-_.-4.-_O CiO O_ 0 C 0 .9-0 _

7"" o T_o

2_ .0_,.. = =_o=o= ,....,..,..,..,..i= ©= =_"-...10_:D _ 0"

0 • • ._

'78

i::__-.-.-.-.-.-.-.-.=-r,vl ..-;- -.=.._ _-i RTR 174:.01

I

i

!

g.ddd e

I "-

d

L i

,_ 1"9 oooocooo..ooo

._ _ _,..

_ _rl 4" ,,1"

oooo_;ooooooill ,._j U.; Qj U,.; _jjO000_lo 0_0

. ,; ,_... •

"':" ,,.* -T: _ O (:i "J" _O

_ I IiI; I I I I li Iti

...., ._. .

o,,4 J e-i

I I I I I I I I I: I I

_; _._o,_... .

• • • II • ID

.,_,,'i_','i_ TM_'I_e'__

I

I

__0

1ii

o OOOO

i

It_tl

000000

moNm_

I

jj_3_lt

__o_

iI

ggdoog

N_NN

iI

0000

ooooo_oo'_o_oo_e_..I I I_ I I I I I I; I / t I I' I

00000_ 0000 O0

q_ I •

I i I: I I '1 I I I I I I I I i; I

IIi

__=_°___.

_. .

oeo_ llO01:l

I i

T9

I_'1_ M-r" _; _ I_ RTR 174-01

Table 5 Cont: Light Weight Tank Design Trajectory Parameters

b) Dispersed Angle of Attack and Yaw

TIME

(Sec)0.0

I0.0

20.0

30.0

40.0

50.0

60.0

70.0

74.0

78.0

82.0

86.0

90.0

94.0

98.0

102.0

106.0

110.0

114.0

118.0

122.0

126.0

130.0

140.0

150.0

160.0

180.0

200.0

220.0

240.0

260.0

288.0

304.0

ALTITUDE

(Ft)519.3

1350.0

4295.7

9581.5

17023.3

VELOCITY

(Ft/Sec)0.0

183.0

429.5

709.4

965.3

(Deg)0.00

0.11

2.61

-3.21

-2.89

i

C_

(Deg)

0.00

-1.42

0.48

-4.44

-3.48

(Deg)0.00

1.23

-4.22

-2.56

-0.35

25837.2

35558.0

46584.6

51534.0

56809.0

62406.7

68314.8

74541.1

81078.6

87906.3

94998.7

102327.3

1182.7

1434.6

1814.1

1999.1

2205.7

2423.4

2656.1

2900.6

3153.8

3421.7

3705.3

3994.7

-2.76

-2.29

-0.01

0.04

0.79

0.41

-0.89

-1.13

-0.96

-0.85

-0.82

-0.84

-4.41

-3.78

-3.01

-2.42

-1.73

-0.76

-1.27

-1.62

-1.64

-1.59

-1.57

-1.63

-0.76

-0.61

-1.23

-1.28

-1.63

-1.86

-2.11

-1.95

-1.31

-0.98

-1.09

-0.94

109862.6

117556.8

125222.7

132732.9

140035.2

147135.3

164126.2

180020.3

194993.6

222846.8

248078.1

270899.5

291526.9

310114.3

331749.8

341337.6

4292.8

4534.5

4664.6

4753.7

4829.4

4932.4

5160.7

5399.5

5622.2

6102.1

6669.4

7310.3

8018.9

8797.8

9526.4

9982.1

-0.95

-0.51

0.75

1.53

0.74

-0.02

-1.53

-10.08

-10.36

-11.04

-11.25

-11.02

-10.35

-16.20

-14.94

-14.68

-1.70

-1.72

-1.58

-1.80

-3.00

-4.29

-5.52

-13.11

-11.95

-12.41

-12.48

-12.13

-11.36

-17.03

-15.88

-15.39

-0.42

4.81

0.61

0.11

0.02

-0.18

-2.42

-6.05

-5.97

-4.85

-4.26

-3.81

-3.42

-5.66

-4.67

-4.26

(Oeg)

0.00

-0.58

-5.89

-3.62

-2.02

-2.03

-2.07

-1.86

-2.12

-2.61

-3.46

-4.61

-5.10

-4.94

-4.51

-4.52

-3.09

-3.30

-6.99

-4.93

-5.15

-6.47

-6.91

-11.58

-15.50

-14.27

-12.24

-10.47

-8.94

-7.57

-12.32

-11.83

-11.38

8O

I=_E M "T- E C I---I RTR 174-01

Table 5 Conc: Light Weight Tank Design Trajectory Parameters

b) Dispersed Angle of Attack and Yaw

TIME

(Se )320.0

336.0

368.0

384.0

400.0

416.0

432.0

464.0

480.0

496.0

528.0

544.0

560.0

576.0

592.0

611.0

ALTITUDE

(Ft)

349089.8

355135.3

362641.8

364346.5

364871.5

364388.3

363077.3

358763.2

356195.5

353677.2

VELOCITY

(Ft/Se¢)10468.1

10986.2

12123.8

12740.9

13398.5

14100.5

14850.8

16517.5

17446.8

18450.8

o_+

(Deg)

-14.00

-13.17

-11.31

-10.21

-8.98

-7.65

-6.22

-3.58

-2.18

-0.73

o:

(Oeg)

-15.39

-13.99

-12.28

-II.31

-10.24

-9.11

-7.91

-4.84

-3.21

-1.56

(Deg)

-4.26

-3.42

-2.53

-2.12

-1.73

-1.32

-0.92

-0.06

0.44

0.97

349904.3

349275.7

349943.8

352229.1

355886.6

360134.5

20726.9

22027.3

23464.2

24992.4

25563.1

25557.9

2.24

3.82

5.38

6.91

7.30

7.27

1.70 2.27

3.39 3.20

5.02 4.48

6.29 6.05

6.56 5.94

6.53 5.93

(Deg)

-11.38

-10.56

-9.83

-9.48

-9.15

-8.82

-8.52

-7.94

-7.70

-7.47

-7.13

-7.04

-7.08

-7.17

-7.40

-7.41

81

]:_ _" M-I- _: C 1--4 RTR 174-01J

Table 6: Methodology - Nose Spike and Nose Cone Points

• Computer Code - LANMIN

Body Section Shock Shape Surface Pressure30 ° Cone 30 ° Cone 30 ° Cone

10 ° Cone 30 ° Cone 10 ° Cone

40 ° Cone 39.38 ° Cone 39.38 ° Cone

• Boundary Layer Transition CriteriaTurbulent Re° > 94

M1Transitional 47 < _ < 94

-- _r I

Laminar g_tt < 47M1

• Laminar Heat Transfer Method - Eckert

• Turbulent Heat Transfer Method - Spaulding Chi

• Rarefied Option Used - Switching Criteria from Boundary Layer to Rarefiedto Free Molecular

M_A = Ze(p_.)o.5 Flight Regime Selection

Parameter

If A __ 0.05 Boundary LayerIf 0.05 < A < 3.0 Rarefied

If A > 3.0 Free Molecular

Moo = Free Stream Mach Number

Reoo, = Free Stream Reynold's Number Based on Running

Length

Ze = Post Normal Shock Compressibility

• Roughness Factor = 1.0

• Mangler Factors (2D to Axisymmetrie) - Boundary Layer Only

Laminar NL = 3

Turbulent NT = 2

• Wall Temperature = 460 ° R.

• Natural Atmosphere - Vandenburg Hot

• Trajectory - LWT Thermal Design Trajectory (1980)

82

I=_ EE: I'v'l-I- E C F--I RTR 174-01

Table 7: Methodology - L02 Tank Points

• Computer Code - ETCHECK

• Shock Shape - 39.38 ° Cone

• Surface Pressure - REMTECH Empirical Curve Fits For ET

• Boundary Layer Heat Transfer Methods

Laminar- Eckert

Turbulent - Spanlding Chi

• Reynolds Analogy - Colburn

• l_oughness Factor - 1.3 for Ogive

- 1.1 for Ogive Barrel

• Boundary Layer Transition Criteria

Turbulent Re

ReTransitional 47 _< _ _< 94

Laminar _ < 47M1

• Mangler Factors (2D to Axisymmetric) - Boundary Layer Only

Laminar NL = 3

Turbulent N T = 2

• Wall Temperature = 460 ° R

• Trajectory - LWT Thermal Design Trajectory (1980)

• Natural Atmosphere - Vandenburg Hot

83

I=_ E M -I" E C I---I RTR 174-01

Table 8: Methodology - Intertank Points

• Computer Code - ETCHECK

• Shock Shape - 39.38 ° Cone

• Surface Pressure - I_MTECH Empirical Curve Fits For ET

• Boundary Layer Heat Transfer Methods

Laminar - Eckert

Turbulent - Spaulding Chi

• Reynolds Analogy - Colburn

• Roughness Factor - 1.15

• Boundary Layer Transition CriteriaTurbulent Ree > 94

M1Transitional 47 < _ < 94

-- M1 --

Laminar Re0 < 47M1

• Mangler Factors (2D to Axisymmetrlc) - Boundary Layer Only

Laminar Nz = 3

Turbulent NT = 2

• Stringer Factors

Minor Crossflow - Equation Page 11 Section 4.3.3

Major Crossflow - Uses the Table Below:

Moo

1.0

3.0

4.0

5.3

Stringer/Waviness Factor

1.00

1.28

1.37

1.46

• Flight/Wind Tunnel Scaling Factors Were Used For Some Body Points

• Wall Temperature - 460 ° tt

• Trajectory - LWT Thermal Design Trajectory (1980)

• Natural Atmosphere - Vandenburg Hot

84

F_EMTEC I--! RTR 174-01

Table 9: Methodology - LH2 Tank Points

• Computer Code - ETCHECK

• Shock Shape - 39.38 o Cone

• Surface Pressure - REMTECH Empirical Curve Fits For ET

• Boundary Layer Heat Transfer MethodsLaminar- Eckert

Turbulent - Spaulding Chi

• Reynolds Analogy- Colburn

• Roughness Factor - 1.1

• Boundary Layer Transition Criteria

Turbulent _ > 47M1

Laminar _ < 47M1

• Mangler Factors (2D to Axisymmetric) - Boundary Layer Only

Laminar Nr, = 3

Turbulent NT = 2

• Wall Temperature = 460 o tt

• Trajectory - LWT Thermal Design Trajectory (1980)

• Natural Atmosphere - Vandenburg Hot

85

I_ !_ M"T I_ C I--I RTR 174-01

Table 10: Rarefied Flow Sharp and Blunt Cone Heat Transfer Equations

1. T._ = Tw + (T6 + Tw)/2 - T6 cos 2 ec/3

2. Re_ = g_u_x

3. C* = ar-__6T_

.gcH4. '7 = (,_2oc+P_ _o,20c/p_.s,vu_)._

5. "Xc = Re_ZeM_ Y_ C,cos 0C

. Correlation Equation

logl0(_)= r_3i = o_i(logl0Xc) _

ao = -0.344074

Sharp az = -0.349130a2 = -0.104455

a3 = +0.022766463

7. Heat Transfer

q = poouooc_(_o - _w)

a0 = -0.647813

az = -0.365587

a2 = -0.0143793

a - 3 = +0.003281793

86

F=_Er,,_--r-=-c_-4 RTR 174-01:

,?

.. 1.00

Q

U

÷

Q

'1:

_ O.lO

0.010.01 0.10 1.0

Sharp Cone Heat Transfer Data

.___.. _ _,-::I .

I_--"; -_ "'--_"I._--;_::-.-:i_ Least Squares _-

._:.__:-_._:.-_!*._--

•_.l- '_@ --I:

r ."'

'_-I-_.

"a),er Theory'=r.: I'_ L;_._. i-"-'[:-: --'_

i - ,

,, • I .-I ' " 1

:.... !':t'rl_- i..'_.... ; -.: .[

1000

Nomenclature

Subscripts

Cg Stanton Number

H Enthalpy

Moo Free Stream Mach Number

T . TemperatureUZ

P

7

/z

Velocity

Post Normal Shock Compressibility

Density

Specific Heat Ratio

Viscosity

W50

Free Stream

WallPost Normal Shock

Total

87

F:_ E: r,,_-l- E: C I---I RTR 174-01

TABLE II: TYPICAL EXAMPLE OF HI/H_ INPUT

BODY PT 7420 T/C 623

XT=1102,6, THETAT= 0.0

M(t)=I,0, HI/HU=I. PHASE t

ALPHA ( BETA

, HI/HU

, OITIS ' OIT

' MACH= 3.! MACH= 4.! MACH= 4.! MACH=5.3

-5. t --9 •

t --_3.

t 3.

s 6,

t 9.

' 3.25 ' 4,05 ' 4, t3 ' 3.92

' 3.14 ' 3.98 ' 3.97 ' 4.00' 3.05 ' 3.77 ' 3,76 ' 4.08

' 2.9B ' 3,50 ' 3,50 ' 4.08

' 2.72 ' 3.2.5 ' 3.26 ' 4.08

' 2.55 ' 4.12 ' 4,12 ' 4.57

' 2.55 ' 5.12 ' 5,10 ' 6.14

O.' -9. ' 3.53 ' 3.28 ' 3.28 ' 4.98

' -5, ' 3.53 I 3,52 ' 3,60 ' 4.74

' -3. ' 3.19 ' 3.72 r 3.72 ' 4._0

' 0, ' 2,84 I 3,28 ' 3,28 ' 4.75

' 3. ' 3.0B ' 3.76 ' 3.75 ' 4.32

' 6, ' 3.48 ' 3.52 ' 3,53 ' 5.57' 9, ' 3.4=4 ' 4,35 ' 4,33 ' 6.Oh

. ! --9.

! m_,,

t _3J

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' 2.72 ' 2.90 ' 2.90 ' 3.92

' 2.70 ' 2.96 ' 2.97 ' 3.87

' 2.9_ ' 3.05 ' 3.03 ' 3.81

' 2.73 ' 3,03 ' 3,03 ' 4.70

' 2.73 ' 3.30 ' 3.30 ' 3.45

-PHASE" 2

M ! HI/HU

4,0 ' 7.7

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TABLE 14: AEROHEATING AND PLUME CONVECTION MAX HEATING

RATE SUMMARY FOR BODY POINT LOCATIONS XT _> 1872

Body XT 8T

Point

7830 1872.20 0.0

7839 1872.20 180.0

7837 1872.20 225.0

7836 1872.20 247.5

7835 "1872.20 270.0

7834 1872.20 292.5

7832 1872.20 315.0

7831 1872.20 337.5

7850 1898.04 0.0

7859 1898.04 180.0

7855 1898.04 270.0

7852 1898.04 315.0

1406 1914.65 304.0

1409 1914.65 315.0

51308 1916.00 30.9

51309 1916.00 30.9

51311 1916.00 30.9

1414 1936.79 330.2

6632 1955.30 23.5

6633 1962.78 23.5

6634 1968.39 23.5

6637 1971.66 23.5

6638 1976.81 23.5

6639 1980.31 23.5

6640 1984.05 23.5

6909 1999.54 19.0

51608 2028.00 30.9

Aeroheating*

REMTECH RI

Max Heating Max HeatingRate Rate

2.42

1.38

1.30

1.32

1.46

1.94

1.85

1.27

1.70

1.23

1.88

1.79

5.47

2.97

2.17

2.36

1.63

3.74

1.96

2.03

2.08

2.11

1.07

1.07

1.07

2.27

6.50

1.99

1.34

1.38

1.13

3.15

4.24

1.75

1.55

2.77

1.53

1.98

2.40

5.39

3.07

2.08

2.24

1.57

3.51

1.11

1.39

1.75

2.96

0.81

0.93

0.91

2.32

6.05

Plume Conv.

RI

Max HeatingRate

3.91

3.65

3.65

3.91

3.91

3.91

3.91

3.91

3.91

3.65

3.65

3.65

3.91

3.91

3.91

3.91

3.91

3.91

3.91

3.91

3.91

3.91

3.91

3.91

3.91

3.91

Method to use when

96 sec < t _< 126 sec

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Aeroheating

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Aeroheating

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Aeroheating

Plume Convection

106

F=__ M"_- _" C P-_ RTR 174-01

TABLE 14 CONC:

AEROHEATING AND PLUME CONVECTION MAX HEATING

RATE SUMMARY FOR BODY POINT LOCATIONS XT _> 1872

Body X T 8T

Point

51609

51611

1021

1300

6647

6929

7920

7929

7925

7922

7921

1041

1023

1043

1025

1205

1303

1046

7930

7939

7937

1054

7935

1032

1211

7931

1307

. 1309

Aeroheating*

REMTECH RI

Max Heating Max Heating

Rate Rate

2028.00 30.9 7.07

2028.00 30.9 4.80

2031.65 289.5 4.65

2032.00 355.0 7.86

2033.00 23.5 7.47

2036.45 19.0 10.60

2036.46 0.0 5.49

2036.46 180.0 1.38

2036.46 270.0 3.57

2036.46 315.0 1.92

2036.46 337.5 2.87

2040.76 250.5 2.65

2048.45 289.5 5.46

2048.75 250.5 3.43

2052.65 289.5 9.14

2053.50 312.6 7.08

2053.50 355.0 9.68

2053.75 250.5 6.76

2058.00 0.0 3.52

2058.00 180.0 1.06

2058.00 225.0 1.24

2058.00 247.0 6:51

2058.00 270.0 6.96

2058.00 283.9 7.00

2058.00 319.4 6.96

2058.00 337.5 6.72

2058.00 357.1 9.41

2058.00 358.8 9.01

6.38

5.02

5.26

8.42

7.62

11.14

5.88

1.41

3.62

2.00

3.51

3.26

5.21

4.39

9.09

6.97

9.24

6.92

3.02

1.00

1.05

6.49

3.50

8.39

7.99

1.98

9.21

9.34

Plume Cony.

RI

Max Heating

Rate

3.91

3.91

3.91

3.91

3.91

3.91

3.91

3.65

3.91

3.91

3.91

3.91

3.91

3.91

3.91

3.91

3.91

3.91

3.91

3.65

3.65

3.91

3.91

3.91

3.91

3.91

3.91

3.91

Method to use when

96 see < t < 126 secN

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convection

Plume Convcctlon

Plume Convection

Plume Convection

Plume Convection

* Note: The aeroheating max. heating rates are for time < 95 seconds.

107

l=_ -.-.-.-.-.-.-.-.-.-_-r,,,,l-n- Ez: _ I--i RTR 174-01

Table 15: Body Points at which Environments did not Favorably Compare Be-

tween KI IVBC-3 and REMTECH

B.P.

70500

70550

70575

70600

70650

70675

71363

71369

71381

71388

71394

II00

1107

6427

7302

7324

7352

7355

7364

7385

7386

7404

7405

7406

7425

1401

6582

7694

7931

7935

XT

(inches)

324.24

345.0

513.60

1111.85

1111.85

1102.62

884.85

929.10

973.40

961.20

1006.70

1038.00

1025.80

1069.40

1102.62

1822.4

1127.6

1615.7

2058.0

OT

(deg.)

0.0

180.0

270.0

0.0

180.0

270.0

225.0

247.5

292.5

315.0

337.5

343.0

348.0

29.0

315.0

292.5

315.0

270.0

292.5

270.0

247.5

292.5

270.0

247.5

270.0

309.4

23.5

292.5

337.5

270.0

LOCATION

40 ° Cone

LO2 Tank

Intertank

LH2 Tank

108

F_ EM "T'EC !--_ RTR 174-01

Table 16: Overview of Net Spray Application Tolerances

* Source: Ref. 12

Surface Geometry CPR Tolerance*Flat

Cylinder

LO2 Fwd Ogive

LO2 Aft OgiveIntertank

Skin/StringerThrust Panel

Intertank (Smooth)

4- 0.25

4- 0.55

4- 0.38

4- 0.55

+ o.3s/- 1.oo+ o.3s/- o.7o

CPR-488 over BX -250

Domes:

LH2 Aft Dome

LH2 Fwd Dome

Aft Dome

4- 0.55

4- 0.25

4- 0.25

+ o.5o/-0.25

109