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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
ii
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
111
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
iv
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
v
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
vi
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.
1
!=_ 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.
3
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_
5
!_ 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
6
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
7
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.
9
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
10
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 _,_ _ _ _._ ,-_ _ ,-, _ ,-,
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F=__ r',_-r'_: C _--.I RTR 174-.01
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-_ 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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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_
!
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??_???
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_._.._ 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 _
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2_ .0_,.. = =_o=o= ,....,..,..,..,..i= ©= =_"-...10_:D _ 0"
0 • • ._
'78
i::__-.-.-.-.-.-.-.-.=-r,vl ..-;- -.=.._ _-i RTR 174:.01
I
i
!
g.ddd e
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L i
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I
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i
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I
jj_3_lt
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iI
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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
s O.
I 3.
I 6.
I 9.
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' 3._B ' 2.72 ' 2,72 ' 4.0t
' 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
9,5 ' 7.7
10.0 ' 7,0
11,0 ' 3.0
25,0 ' 3,0
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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