NASA TECHNICAL

I -- -jlow fields

Held at

Ames Research Ceater

Moffett Field, Califoroia

15-16, 1971

HATJOiAl AIROHAUTICS AHD SPACE ADMINISTRATION • WASHJH6T0N, B. C. - FIBIOA8Y J972

https://ntrs.nasa.gov/search.jsp?R=19720013197 2020-01-13T17:52:20+00:00Z

- I4

1. Report No. 2. Government Accession No.

NASA TM X-2506

4. Title and Subtitle

SPACE SHUTTLE AEROTHERMODYNAMICS TECHNOLOGY CONFERENCEVOLUME I - FLOW FIELDS

7. Author(s)

9. Performing Organization Name and Address

NASA Langley Research CenterHampton, Va. 23365

12. Sponsoring Agency Name and Address

National Aeronautics and Space AdministrationWashington, B.C. 20546

3. Recipient's Catalog No.

5. Report DateFebruary 1972

6. Performing Organization Code

8. Performing Organization Report No.L-8156-.

10. Work Unit No.

11. Contract or Grant No.

13. Type of Report and Period Covered

Technical Memorandum

14. Sponsoring Agency Code

15. Supplementary Notes

Held at NASA Ames Research Center, December 15-16, 1971.

16. Abstract

The conference encompasses four technology efforts, each published as a separate volume.

Volume I - Flow Fields (NASA TM X-2506)

Volume II - Heating (NASA TM X-2507)

Volume III - Aerodynamics (NASA TM X-2508)

Volume IV - Operational Flight Mechanics (NASA TM X-2509)

17. Key Words (Suggested by Author(s)) 18. Distribution StatementFlow fieldsHealingAerodynamics Unclassified - UnlimitedOperational flight mechanicsSpace shuttleAerothermodynamics

19. Security dassif. (of this report) 20. Security Classif. (of this page)

Unclassified Unclassified

21. No. of Pages 22. Price*

270 $3.00

For sale by the National Technical Information Service, Springfield, Virginia 22151

Page intentionally left blank

PREFACE

A Space Shuttle Technology Conference on Flow Fields, Heat Transfer, Aero-

dynamics, and Operational Flight Mechanics was held at the NASA Ames Research

Center on December 15 and 16, 1971- The objective of this conference was to

review the broad base of aerothermodynamics technology developed for the space

shuttle during the period of the Phase B studies and, thereby, help focus

attention on the technology required for further space shuttle development.

This publication is a compilation of the conference papers. It has been divided

into four volumes, one for each of the sessions. Five papers which were omitted

from the oral presentation at the conference are included in this publication.

Contributing organizations include U.S. Aerospace Contractors, Universities,

Canadian and European Space Agencies, in addition to NASA Research Centers/

iii

Page intentionally left blank

CONTENTS

GLOSSARY IX

OPENING REMARKS

1. SHUTTLE PROGRAM STATUS 1Edward P. Andrews, NASA Headquarters

2. SHUTTLE TECHNOLOGY - INTRODUCTORY REMARKS laA. 0. Tischler, NASA Headquarters

VOLUME I.- FLOW FIELDS

3- INTRODUCTION 1^5Joseph G. Marvin, ARC

k. DETERMINATION OF SPACE SHUTTLE FLOW FIELD BY THETHREE-DIMENSIONAL METHOD OF CHARACTERISTICS If7Chong-Wei Chu and S. A. Powers, Northrop

5- APPLICATION OF SHOCK CAPTURING AND CHARACTERISTICS METHODSTO SHUTTLE FLOW FIELDS 65P. Kutler, J. V. Rakich, and G. G. Mateer, ARC

6. FLOW FIELD PREDICTIONS FOR A SLAB DELTA WING AT INCIDENCE 93R. J. Conti, P. D. Thomas, and Y. S. Chou, Lockheed

7. SPACE SHUTTLE ORBITER REENTRY FLOW FIELD AND HEATING ANALYSIS 115W. C. Rochelle, TRACOR; B. B. Roberts, MSCj F. W. Vogenitz,and L. d'Attorre, TRW Systems

8. A VISCOUS STARTER SOLUTION FOR SHUTTLE FLOW FIELD COMPUTATIONS .... 157C. P. Li, Lockheed Electronics Co.; and W. D. Goodrich, MSC

9. CHEMICAL NONEQUILIBRIUM EFFECTS ON THE FLOW IN THE WINDWARD PLANEOF SYMMETRY OF A BLUNTED DELTA ORBITER 185J. A. Lordi, R. J. Vidal, Cornell Aeronautical Laboratory;and C. B. Johnson, LRC

10. INVISCID-SURFACE-STREAMLINE PROGRAM FOR USE IN PREDICTINGSHUTTLE HEATING RATES . ..._.. . 23_9_H. Harris Hamilton, LRC; and Fred R. DeJarnette, North CarolinaState University

11. SUMMARY 255Joseph G. Marvin, ARC

VOLUME II.- HEATING

12. INTRODUCTION ............................. 257James C. Dunavant, LRC

13. EXPERIMENTAL AND THEORETICAL AERODYNAMIC HEATING AND FLOW FIELDANALYSIS OF A SPACE SHUTTLE ORBITER ................ 26lR. K. Matthews, T. D. Buchanan, W. R. Martindale, ARO, Inc.;and J. D. Warmbrod, MSFC

Ik. A REVIEW OF THE GRUMMAN ORBITER WIND TUNNEL HEAT TRANSFER TESTS . . . 297A: R. Mendelsohn, M. Bourbin, M. Jew, and C. W. Osonitsch, Grumman

15. HIGH REYNOLDS NUMBER TURBULENT HEATING TO TWO SIMPLIFIEDSHUTTLE CONFIGURATIONS ......... ........... . .Charles B. Johnson, LRC

16. EFFECTS OF ROUGHNESS ON HEATING AND BOUNDARY -LAYER TRANSITIONI. EFFECTS OF SIMULATED PANEL JOINTS ON BOUNDARY-LAYER

TRANSITION .................. ': ....... 375H. Lee Seegmlller, ARC

II. EFFECTS OF DISCRETE ROUGHNESS ON HEATING ............ 395George G. Mateer, ARC

17. LEE -SIDE FLOW PHENOMENA ON SPACE SHUTTLE CONFIGURATIONS ATHYPERSONIC SPEEDSI. FLOW SEPARATION AND FLOW FIELD VISCOUS PHENOMENA OF A

DELTA-WING SHUTTLE ORBITER CONFIGURATION ...........J. W. Cleary, ARC

II. STUDIES OF LEE -SURFACE HEATING AT HYPERSONIC MACH NUMBERS . . .Jerry N. Hefner and Allen H. Whitehead, Jr., LRC

18. AEROTHERMODYNAMIC MEASUREMENTS FOR SPACE SHUTTLE CONFIGURATIONSIN HYPERSONIC WIND TUNNELS .....................John J. Bertin, Frank E. Williams, Robert C. Baker, Universityof Texas; Winston D. Goodrich, MSC; and William C. Kessler,McDonnell Douglas

19. DETERMINATION OF AEROTHERMODYNAMIC ENVIRONMENT UNCERTAINTIESWITH APPLICATION TO SPACE SHUTTLE VEHICLES ............. 503C."f A. Scottoline, North American Rockwell

20. SPACE SHUTTLE BOOSTER MULTI-ENGINE BASE FLOW ANALYSIS ........ 519Homer H. Tang, Charles P. Gardiner, William A. Anderson, andJohn Navickas, McDonnell Douglas

21. AN ANALYSIS OF THE BOOSTER PLUME IMPINGEMENT ENVIRONMENT DURINGTHE SPACE SHUTTLE NOMINAL STAGING MANEUVER ............. . 607C. J. Wojciechowski, M. M. Penny, Lockheed - Huntsville;T. F. Greenwood, MSFC; and I. H. Fossler, MSC

VI

22. CONNECTIVE HEATING MEASUREMENT BY MEANS OF AN INFRARED CAMERA . . . .Dale L. Compton, ARC

23- HEAT-TRANSFER TESTING PROCEDURES IN PHASE B SHUTTLE STUDIESWITH EMPHASIS ON PHASE-CHANGE-DATA IMPROVEMENT 66lDavid A. Throckmorton, LRC

2k. EVALUATION OF BOUNDARY-LAYER-TRANSITION CRITERIA FOR SPACESHUTTLE ORBITER ENTRY . . . 683Vernon T. Helms III, LRC

VOLUME III.- AERODYNAMICS

25. INTRODUCTORY REMARKS OF SESSION CHAIRMAN .............. 705Beverly Z. Henry, LRC-

26. STATUS OF LANGLEY STUDIES OF AERODYNAMICS AND INTERFERENCE EFFECTSOF TANDEM LAUNCH VEHICLES ..................... 707William I. Scallion and Kermit G. Pratt, LRC

27. IMPACT OF SUBSONIC AERODYNAMIC CONSIDERATIONS ON A SPACE SHUTTLEBOOSTER CONFIGURATION ....................... 737R. L. Roensch, Douglas Aircraft Co.; and R. L. Odenbaugh,McDonnell Douglas Astronautics Co. - West

28. AERODYNAMIC STUDIES OF DELTA-WING SHUTTLE ORBITERSI. LOW SPEED ........................... 785

Delma C. Freeman, Jr., and James C. Ellison, LRCII. HYPERSONICS .......................... 803

Howard W. Stone and James P. Arrington, LRC

29- WING OPTIMIZATION FOR SPACE SHUTTLE ORBITER VEHICLES . . ...... 831T. E. Surber, W. E. Bornemann, and W. D. Miller, NorthAmerican Rockwell

30. REVIEW OF DELTA WING SPACE SHUTTLE VEHICLE DYNAMICS ......... 861J. Peter Reding and Lars E. Ericsson, Lockheed

31. EXPERIMENTS ON THE DYNAMIC STABILITY OF THE SPACE SHUTTLE ..... . .933K. J. Orlik-Ruckemann, J. G. LaBerge, and E. S. Hanff, NationalResearch Council of Canada

AePOTENTIAL PARTICIPATION IN THE DEVELOPMENT OF THE SPACE SHUTTLEORBITER 969M. Fuchs, J. Haseloff, and G. Peters, ERNO

33- SUMMARY REMARKS OF SESSION CHAIRMAN 993Beverly Z. Henry, LRC

vii

VOLUME IV.- OPERATIONAL FLIGHT MECHANICS

3U. INTRODUCTION ............................. 997Victor L. Peterson, ARC

35 . VEHICLE PERFORMANCE IMPACT ON SPACE SHUTTLE DESIGN ANDCONCEPT EVALUATION ........... ............. 999Mark K. Craig, MSC

36. SPACE SHUTTLE ATMOSPHERIC ASCENT FLIGHT DYNAMICS ........... 1041J.. T. Patha, K. A. Noess, and M. V. Lines, Boeing

,7

37. OPTIMAL LIFTING ASCENT TRAJECTORIES FOR THE SPACE SHUTTLE ...... 1063T. R. Rau and J. R. Elliott, LRC

38. OPTIMAL ASCENT TRAJECTORIES OF A TWO STAGE SPACE SHUTTLE VEHICLE . . . 1089R. A. Wilson, North American Rockwell

39. ABORT SEPARATION OF THE SHUTTLE ................... 1105John P. Decker, LRC; Kenneth L. Blackwell, Joseph L. Sims, MSFC;R. H. Burt, W. T. Strike, Jr., AROj C. Donald Andrews, L. RayBaker, Jr., LMSC - Huntsville; and John M. Rampy, Northrop -Huntsville

hO. BOOSTER RECOVERY FOLLOWING PREMATURE SPACE SHUTTLE STAGESEPARATION ............................. 1165M. J. Hurley, General Dynamics /Convair

111. EFFECT OF COMMERCIAL AND MILITARY PERFORMANCE REQUIREMENTS FORTRANSPORT CATEGORY AIRCRAFT ON SPACE SHUTTLE BOOSTER DESIGNAND OPERATION ........................... 1191R. A. Bithell and W. A. Pence, Jr., General Dynamics /Convair

42. SPACE SHUTTLE ORBITER HANDLING QUALITY CRITERIA APPLICABLE TOTERMINAL AREA, APPROACH, AND LANDING ................ 1239Gordon H. Hardy, ARC

43- ORBITER ENTRY TRAJECTORY CONSIDERATIONS . . . . ........... 1265John J. Rehder and Paul F. Holloway, LRC

44. STAGE SEPARATION OF PARALLEL -STAGED SHUTTLE VEHICLES,A CAPABILITY ASSESSMENT ...................... 1301M. " J. Hurley and G. W. Carrie, General Dynamics /Convair

45. SPACE SHUTTLE BOOSTER FLYBACK SYSTEM SYNTHESIS ............ 1397D. W. Jones, W. J. Moran, and V. A. Lee, General Dynamics /Convair

. OPTIMIZED SPACE SHUTTLE TRAJECTORY SIMULATIONLouis Tramonti and Richard G. Brusch, General Dynamics /Convair

van

GLOSSARY

ABES

i AC PS

AEDC

AFB

AFFDL

ALT

APS

AR

ARC

ARDC

BECO

BLOW

BV

BW

BWV

CAL

CALCS

CAL HST

CFHT

CG; C.G.; e.g.

CONFIG

~CRT

Cyl

2-D

3-D

air breathing engines

attitude control propulsion system

Arnold Engineering Development Center

air force basei

Air Force Flight Dynamics Laboratory

altitude

auxiliary propulsion system

aspect ratio

Ames Research Center

Air Research and Development Command

booster engine cutoff

booster lift-off weight

body-vertical tail

body-wing

body-wing-vertical tail

Cornell Aeronautical Laboratory

calculations

Cornell Aeronautical Laboratory hypersonic shock tunnel

continuous-flow hypersonic tunnel

center of gravity . •

configuration7

"cathode ray tube

cylinder

two-dimensional

thr e e-dimens i onal

IX

DAC

DCM

DEX .

DIA

DIAT -

DIF. KEFL.

JDMoC

DOD

DOF

DWO

EHT

EOHT

EPL

EST

ETR

F&M

FAR; F.A.R.

FBS

F.D.

F/0

FO/FS

FPR

FPRE

FR

FREQ

GAG

Douglas Aircraft Company

data control management

exit diameter

diameter

diatomic

differential deflection

three-dimensional method of characteristics

Department of Defense

degrees of freedom

delta-wing orbiter

external hydrogen tank

external oxygen-hydrogen tank

emergency power level

estimated

eastern test range

force and moment

Federal Aircraft Regulation

flyback system

finite difference

fuel-oxygen ratio

fail operational/fail safe

flight performance reserve

flat-plate reference enthalpy

fully reusable

frequency

Grumman Aerospace Corporation

x

GD

GDC

GD/C

G.-E.

GLOW

GTOP

GW

H

HCF

HCR

HeT

HO

H.W.T.

IAC

IBFF

ICD

IFR .

ILRV

ILS

USD

IR

IRAD

KSC

General Dynamics

General Dynamics Corporation

General Dynamics/Convair

General Electric Company

vehicle gross lift-off weight

general trajectory optimization program

gross weight

hydrogen

highly compacted fibers

high cross range

Mach 20 helium tunnel

hydrogen-oxygen system

hypersonic wind tunnel

industrial air center

impulse base flow facility

interface control drawing

instrument flight rules

integral launch and reentry vehicle

instrument landing system

industrial

infrared

Independent Research and Development

Kennedy Space Center

L.E.

LEE

leading edge

leeward

liquid hydrogen

XI

LMSC

L02; LOX

LRC; LaRC

LRU

MAC

MAC Exp

MARK I, MARK II

MAX

MC

MCAIR

MCAS

MDAC

MDC

MIL SPEC

MIN

MM HWT

MOC

MPL

MSC

MSFC

MT.

NA

NAE; N.A.E.

NAR; NARC; NR

WAS

NASA

Lockheed Missiles & Space Company

liquid oxygen

Langley Research Center

link retraction unit

mean aerodynamic chord

exposed mean aerodynamic chord

shuttle configurations

maximum

Monte Carlo

a low-speed wind tunnel

Marine Corps Air Station

McDonnell Douglas Astronautics Company

McDonnell Douglas Corporation

military specification

minimum

Martin Marietta Corporation hotshot wind tunnel

method of characteristics

minimum power level

Manned Spacecraft Center

Marshall Space Flight Center

mountain

North American

National Aeronautical Establishment

North American Rockwell Corporation

Naval Air Station

National Aeronautics and Space Administration

xn

NO.; No.

WOZ

NPL

0/F

GLOW

OMS

P/L

PM

RCC

RCS

Eef

REQD

RFP

RGAS

R.H.

RSI

RTV

S&C

SCT

SF

S.L.; SL

SM

_SEEC

SRM

SS

SSV

ST

number

nozzle

normal power level

oxygen-fuel ratio

orbiter lift-off weight

orbiting maneuvering system

payload

pitching moment

reinforced carbon carbon

reaction control system

reference

required

request for porposals

real gas

right hand engine

reusable surface insulation

room-temperature vulcanizing rubber

stability and control

shock capturing technique

stick force

sea level

service module

specification

solid rocket motors

stainless steel

space shuttle vehicle

straight

Xlll

STAR

STD

STI

STOL

SW

SYM

T/C

T.E.

T.E.D.

TEMP

T.E.U.

THEO

TPS

TEAJ

TVC

Typ

UPWT

USAF

VAC HVWT

VAFB

VDT

VFR

V/STOL

w/o

WT

WWD -

YM

strings and array computer; self-testing and repair computer

standard

Systems Technology, Incorporated

short take-off and landing

southwest

symbol

thermocouple

trailing edge

trailing edge down

temperature

trailing edge up

theoretical

thermal protection system

trajectory

thrust vector control

typical

Unitary Plan wind tunnel

U.S. Air Force

Vought Aeronautics Company hypervelocity wind tunnel

Vandenburg Air Force Base

variable density tunnel

visual flight rules

vertical and short take-off and landing

without

weight

windward

yawing moment

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39

Page intentionally left blank

SHUTTLE TECHNOLOGY - INTRODUCTORY REMARKS

By A. 0. Tischler

Director of Shuttle Technologies Office, OARTNASA Headquarters, Washington, D.C.

This conference is the third large conference covering the general subject

of aerothermodynamics for the reusable earth-to-orbit transportation system, '

commonly called the "shuttle," and the first to be devoted exclusively to the

aerothermodynamic problems and issues. The first of these conferences, held at

the Lewis Research Center in the summer of 1970, told everyone what.the approach

to shuttle technology work would be. The second, held at the Langley Research •

Center in the late winter of 1971, made the overall plan more substantive and :

provided some results. This conference, hopefully, will disclose much data and

correlations on the shuttle-related aerothermodynamic technology..

Aerodynamics has played an important role in shaping the shuttle concept.

Even before the formation of NASA in 1958, serious thought was being given to

the idea of an aerodynamically controllable entry and return space vehicle. It

was only a matter of technological state of the art that led to the use of blunt

conical semiballistic reentry bodies for Mercury, Gemini, and Apollo. The' work

that sprang out of these early deliberations, which led NASA to the lifting-body

programs, and more importantly, led the U.S. Air Force to sponsor the DynaSoar

project, on which some $i+OOM were spent, along with continuing technology work by

the Flight Dynamics Laboratory at the Wright Patterson Air Force Base, gave a con-

siderable background for flyable reentry vehicles. This work, the improved high-

performance propulsion systems being developed by both NASA and Air Force, and

the improvements in refractory materials resulting from a broad frontal research

attack, laid alongside the high present cost of injecting payloads into space,

paved the way for accepting the idea that the time to start developing a reusable

space vehicle was at hand.

The shuttle vehicle has, however, encountered severe constraints in its

fiscal diet for the early development years. Consequently, a series of vehicle

design and configuration studies have been made to determine a vehicle design

approach which, for a prescribed mission model, will have least cost in terms

of the present value of money. The systems that are the front runners at this

moment have been described by Edward Andrews (paper no. 1.)

It is probably unnecessary to remind anyone here that the changing config-

urational picture has kept the aerodynamics and aerothermodynamics personnel

busy. The importance of understanding the aerodynamic and aerothermal effects

on the flight mechanics and structural integrity of this three-piece vehicle

during a flight spectrum which ranges from Mach 0 to Mach 25 and back to Mach 0

under continually varying pressure and density cannot be minimized. In spite of

the obvious difficulties one advantage is the fact that the shuttle does not

have to be a superior airplane. As long as it can be adequately controlled

through the flight regime without scorching its skin it would appear to meet the

mandatory requirement s.

Back in the summer of 1969 OMSF and OART began a precedent-setting joint

effort to examine and prepare a technological base to support the shuttle. As

most of you know this program has pulled together the talents of the research

and space flight centers of NASA, has vastly improved communications at the

problem-solving level, and tied in not qmly the contractors, but also the

European technologists who are interested in participating in the post-Apollo

endeavors.

The management approach to this program is to solicit and to use the advice

of seven Working Groups. These Working Groups, of which the Group on

Aerothermodynamics chaired by Arthur Henderson of Langley Research Center is

one, comprise representatives of all NASA Centers engaged in the work activity.

They recommend the program content; they are also actively engaged in monitoring

it. This conference represents one of the Working Group information dissemination

functions. I would like here to express my appreciation to Dr. Hans Mark and his

entire team for organizing and hosting this symposium.

Funding for the technology effort, which will total $1JOM by the end of

FY 1972, is derived from both OART and OMSF fund sources. The Aerothermodynamics

total effort during this period will be $l6M, a sum which does not include the

salary expenses of NASA personnel engaged in the work, nor any contractors'

efforts paid under vehicle configuration studies, nor any of the independent

research and development funds which various companies have been persuaded to

invest in the shuttle prospect. 925 NASA personnel are directly involved in this

technology work; the aerothermodynamics effort accounts for nearly one-fourth of

these personnel.

Some of the results of this work have been noteworthy. New test methods

for studying heat-transfer rates and shock flow and impingement have been invented

out of necessity to handle the large volume of work. The program has now used

about 20 000 wind-tunnel hours. This technical progress will be covered here in

much detail in the next 2 days.

With the coming fiscal.year, NASA anticipates moving the shuttle program into

the design and development phase. This change will require a transition of many

of our technology investigations into development support. Because of the

intrinsic need to support closely the shuttle configurational design selections,

it seems likely that this aerodynamic work effort will continue at a high level.

In fact, it is expected that test facilities located in Europe will be used to

relieve the load of work imposed on the U.S. facilities if satisfactory working

relationships can be worked out and it is believed that they will be.

I look forward, along with you, to the development and operation of this

system so vital to a healthy and aggressive space program. I expect that this

conference will be seen in retrospect as a significant contribution to the

development of economical access to the space arena.

FLOW FIELDS SESSION

INTRODUCTION

by

Joseph G. Marvin

NASA Ames Research Center

Vehicle aerodynamics, heating, thermal protection system response,

chemical effects on surface materials, and chemical effects within the

shock layer are a few of the many variables that depend on the flow

field around the Space Shuttle vehicle during its flight through the

atmosphere. A need for flow field calculations arises mainly from the

inability to completely simulate the flight environment in ground-based

facilities. For example, tests performed to simulate the high enthalpies

associated with entry often have the incorrect flow chemistry because of

model scale effects. Therefore, the designer must extrapolate test data by

using the best information about the real flow field. Exact three-

dimensional flow field calculations are now at the threshold of providing

the necessary rationale upon which to base this important extrapolation.

At the last Space Shuttle Technology Conference held at Langley

Field in March 1971, there was only one paper devoted to exact flow

field calculations. In this session there are seven papers, five of

which contain exact methods for computing three-dimensional flow fields.

The remaining two papers treat in an approximate way chemical nonequili-

.brium effects and streamline calculations used as input for heating

estimates. The emphasis on flow fields at this conference developed

mainly from recent technology advances made in exact calculation methods

and in computer storage and speed that is necessary in the practical

application of these methods. The papers were selected in order that

the progress made on shuttle flow field calculations can be judged and

so that future needs can be determined.

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(Figure 1)

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in the radial direction and 19 points in the meridional direction-4

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he integrity of the whole calculation unless every region of the flow is pro-

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ary layer was calculated with a technique developed by

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restriction on the curvature of inviscid streamlines,§ca0CJaJHftca•Hc~j^_jCO0-PG•H•d0O00G•H0-PCO

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REFERENCES

i

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x, H. : "A Description of Numerical Methods and Computer

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Axisymmetric Supersonic Flow over Blunt-Nosed and Flared

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s, NASA/MSC, Houston, Tex.,

RW Systems, Redondo Beach, Calif.,

TRW Systems, Redondo Beach, Calif.

INTRODUCTION

s of a study performed by TRW Systems for NASA/MSC

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. NONEQUILIBRIUM IN THE INVISCID FLOW FIELSURFACE HEATING RATES

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INFLUENCE OF CHEMICALON

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preceding papers provide material from which to form a judgement regarding the status andcuH

eds of exact flow field calculations, as summarized in figure 1.cuc01S-l34-13

t methods are available to provide the starting data for the three-dimensional inviscid

ons used when the flow field is predominately supersonic. At the high altitudes where

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flows for realistic shuttle geometries at angles of attack where the flow is predominately

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