Table Of ContentAEROTHERMODYNAMICS
AND PLANETARY ENTRY
Edited by
A. L. Crosbie
Thermal Radiative Transfer Group
Department of Mechanical and Aerospace Engineering
University of Missouri-Rolla, Rolla, Missouri
Volume 77
PROGRESS IN
ASTRONAUTICS AND AERONAUTICS
Martin Summerfield, Series Editor-in-Chief
Princeton Combustion Research Laboratories, Inc.,
Princeton, New Jersey
Technical papers from the AIAA 18th Aerospace Sciences Meeting. January 1980,
and the AIAA 15th Thermophysics Conference, July 1980, subsequently revised
for this volume.
Published by the American Institute of Aeronautics and Astronautics,
1290 Avenue of the Americas, New York, N.Y. 10104.
American Institute of Aeronautics and Astronautics
New York, New York
Library of Congress Cataloging in Publication Data
AIAA Aerospace Sciences Meeting (18th: 1980:
Los Angeles, Calif.)
Aerothermodynamics and planetary entry.
(Progress in astronautics and aeronautics; v. 77) Bibliography: p.
1. Aerothermodynamics—Congresses. 2 Space vehicles—Atmospheric
entry—Congresses. I. Crosbie, A. L. (Alfred L.) II. AIAA Thermophysics
Conference (15th: 1980: Snowmass, Colo.) III. American Institute of
Aeronautics and Astronautics. IV. Series.
TL1060.A36 1980 629.4'152 81-10785
ISBN 0-915928-52-3 AACR2
Copyright © 1981 by
American Institute of Aeronautics and Astronautics.
All rights reserved. No part of this book may be reproduced in any form or
by any means, electronic or mechanical, including photocopying,
recording, or by any information storage and retrieval system, without
permission in writing from the publisher.
Table of Contents
Preface.............................................. vii
Editorial Committee . . . . . . . . . . . . . . . . . . . . . . . . . . .. ....... x
List of Series Volumes................................. xi
Chapter I. Aero thermodynamics......................... 1
Aerodynamic Heating for Gaps in Laminar and
Transitional Boundary Layers.............................. 3
J. J. Bertin, University of Texas, Austin, Tex., and W. D. Goodrich,
NASA Johnson Space Center, Houston, Tex.
Correlation of Convection Heat Transfer for Open Cavities
in Supersonic Flow ..................................... 36
J. P. Lamb, The University of Texas at Austin, Austin, Tex.
Heat Transfer and Pressure on a Flat Plate Downstream
of a Heated Square Jet in a Mach 0.4 to 0.8 Crossflow......... 51
D. J. McDermott, W right-Patter son Air Force Base, Ohio
The Effect of Surface Roughness Character
on Turbulent Re-entry Heating ............................ 83
M. L. Finson and A. S. Clarke, Physical Sciences Inc., Woburn, Mass.
Three-Dimensional Protuberance Interference Heating
in High-Speed Flow.................................... 109
F. T. Hung, The Aerospace Corporation, El Segundo, Calif., and
J. M. Clauss, Rockwell International Corporation, Downey, Calif.
Hypersonic Flow over Small Span Flaps
in a Thick Turbulent Boundary Layer...................... 137
L. A. Cassel, TRW Defense & Space Systems Group, San Bernardino,
Calif., and T. W. Jarrett, Science Applications, Inc., Irvine, Calif.
iv
Chapter II. Thermal Protection........................ 167
Thermochemical Ablation of Tantalum Carbide Loaded
Carbon-Carbons . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 169
B. Laub, Acurex Corporation/Aerotherm Division, Mountain View,
Calif.
Catalytic Recombination of Nitrogen and Oxygen
on High-Temperature Reusable Surface Insulation............ 192
C. D. Scott, NASA Lyndon B. Johnson Space Center, Houston, Tex.
Particle Acceleration Using a Helium Arc Heater............... 213
J. H. Painter, McDonnell Douglas Astronautics Company-St. Louis
Division, St. Louis, Mo.
Temperature and Ablation Optical Sensor . . . . . . . . . . . . . . . . . . .. 242
J. J. Cassaing, P. M. Lelievre, P. Durrenberger, and D. L Balageas,
ONERA, Chdtillon, France
Wind-Tunnel Study of Ascent Heating
of Multiple Re-entry Vehicle Configurations. ................ 260
R. J. Herman and D. E. Nestler, General Electric Company, Philadelphia,
Pa.
Re-entry Vehicle Soft-Recovery Techniques . . . . . . . . . . . . . . . . . .. 287
D. J. Kigali, and M. W. Sterk, Sandia National Laboratories,
Albuquerque, N. Mex., and J. Randmaa, USAF Ballistic Missile Office,
Norton Air Force Base, Calif.
Chapter III. Planetary Entry.......................... 307
Thermal Protection System for the Galileo Mission
Atmospheric Entry Probe............................... 309
R. A. Brewer and D. N. Brant, General Electric Company, Philadelphia,
Pa.
Viscosity of Multicomponent Partially Ionized Gas Mixtures
Associated with Jovian Entry ............................ 335
B. F. Armaly, University of Missouri-Rolla, Rolla, Mo., and K. Sutton,
NASA Langley Research Center, Hampton, Va.
Coupled Laminar and Turbulent Flow Solutions
for Jovian Entry ...................................... 351
A. Kumar, Old Dominion University, Norfolk, Va., R. A. Graves Jr. and
K. J. Weilmuenster, NASA Langley Research Center, Hampton, Va.,
and S. N. Tiwari, Old Dominion University, Norfolk, Va.
Preliminary Aerothermal Analysis for Saturn Entry............. 374
E. V. Zoby and J. N. Moss, NASA Langley Research Center, Hampton,
Va.
Thermophysical and Systems Integration Considerations
in Aerobraking Design .................................. 396
J. R. French and A. D. McRonald, Jet Propulsion Laboratory, California
Institute of Technology, Pasadena, Calif.
Technology Requirements for a Generic Aerocapture System ..... 412
M. I. Cruz, Jet Propulsion Laboratory, California Institute of
Technology, Pasadena, Calif.
Author Index . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 441
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Preface
Thermal protection of a spacecraft or probe entering a planetary
atmosphere is one of the most challenging problems ever attempted.
The thermal design of these vehicles requires the coupling of heat
transfer and fluid mechanics to predict heating rates. The
development of the Space Shuttle and the advancement of missile
technology have stimulated interest in Earth entry and aero-
thermodynamics, in particular. The Space Shuttle's size and
complex geometry, combined with the fact that it is to be a reusable
spacecraft, give rise to many unique aerodynamic heating problems.
By necessity much of the work in this area is experimental in nature.
Exploration of the other planets in our solar system has also
stimulated interest in entry technology. The high entry velocities and
severe environments challenge our thermal design capabilities. For
example, almost half the weight of the Galileo (Jupiter) probe is
devoted to its thermal protection system. Because of the difficulty of
experimentally simulating the entry conditions here on Earth, most
of the thermal design work for the Galileo probe must be ac-
complished by numerical simulation.
This volume contains a selection of recent studies in aerother-
modynamics and planetary entry. The papers for this volume and its
companion volume were drawn from the AIAA 18th Aerospace
Sciences Meeting in Los Angeles, California in January 1980 and the
AIAA 15th Thermophysics Conference in Snowmass, Colorado in
July 1980. They have been reviewed, revised, and updated especially
for these volumes. The papers in Volume 77 have been grouped into
three chapters: aerothermodynamics, thermal protection, and
planetary entry.
Besides the obvious appeal of this volume to those working in the
area of entry technology, the volume should be of interest to
engineers and scientists working in related areas. Specifically, these
areas include: forced convection heat transfer, gaseous radiation
heat transfer, experimental fluid mechanics, turbulent and tran-
sitional boundary layers, and thermophysical properties of high
temperature gases. Hopefully, the research developments reported
vii
viii
here will stimulate Earth-based technologies which are confronted
with problems of high heating rates and extreme environments.
Chapter I consists of six papers concerned with the influence of
surface geometry on aerodynamic heating. The first two papers deal
with supersonic flow over rectangular gaps or slots. Berlin and
Goodrich measure heating rates in and around various transverse
gap and longitudinal slot configurations in laminar and transitional
boundary layers, while Lamb correlates heat-transfer data for a
transverse gap with laminar or turbulent flow. These studies are
motivated in part by the Space Shuttle. In the third paper,
McDermott reports measurements of local heat-flux rates on a flat
plate downstream of a square, subsonic, hot air jet issuing from the
surface.
The next three papers deal with high-speed flow over surfaces with
protuberances as opposed to gaps or slots. Finson and Clarke
present a Reynolds stress model for studying the influence of
roughness character (element shape and spacing) on skin friction
heat transfer for turbulent boundary layers and high Mach numbers.
Hung and Clarke present an extensive experimental study on in-
terference heating caused by a three-dimensional cylindrical
protuberance protruding from a flat plate. Measurements are made
on both the flat plate and the protuberance. Cassel and Jarrett
report aeroheating measurements for finite span trailing flaps in
hypersonic flow. The flap deflection angles of 5, 10, and 15 deg are
considered.
Various aspects of thermal protection systems are discussed in the
six papers of Chapter II. Laub presents a thermochemical ablation
model for carbon-carbon composite materials loaded with tantalum
carbide. Steady-state ablation predictions are compared with
available arc test data and other existing ablation models. The
energy transfer catalytic recombination coefficient for nitrogen and
oxygen recombination on the surface coating of high-temperature
reusable surface insulation is inferred by Scott from stagnation point
heat-flux measurements in a high-temperature dissociated arc jet
flow.
The next four papers deal with experimental techniques. Painter
uses arc-heated helium to accelerate graphite particles to hyper-
velocities with the objective of simulating the erosion of a thermal
protection system by particles suspended in the atmosphere.
Cassaing, Lelievre, Durrengerger, and Balageas present a novel
IX
combined ablation/temperature gage which uses the optical view of
radiation from a sensor embedded in a heat shield. Herman and
Nestler conduct a wind-tunnel study at Mach 8 to provide design
information for the multiple re-entry vehicle assent heating problem.
A phase-change paint technique is used to identify shock im-
pingement hot spots. Soft-recovery techniques for moderately high
ballistic coefficient re-entry vehicles are discussed by Kigali, Sterk,
and Randmaa.
Chapter III consists of six papers concerned with vehicle heating
during planetry entry. The first three papers deal with Jovian entry.
The thermal design of the Galileo probe is described by Brewer and
Brant. An approximate method is proposed by Armaly and Sutton
for predicting the viscosity of partially ionized gas mixtures. Kumar,
Tiwari, Graves, and Weilmuenster use a time-dependent finite-
difference method for solving the problem of coupled laminar and
turbulent flows over the forebody of a probe entering a nominal
Jupiter atmosphere. Solutions are obtained for both a 35 deg
hyperboloid and a 45 deg sphere cone.
Preliminary studies are given in the next three papers. Using
methods developed for the Galileo probe, Zoby and Moss present a
preliminary thermal analysis on Saturn entry. French andMcRonald
investigate the aerobraking entry technique to reduce space-
craft mass, while Cruz investigates the aerocapture technique.
Aerobraking requires propulsive maneuvers, while aerocapture
relies entirely on atmospheric drag. Both techniques show promise in
increasing scientific payloads by reducing the weight of thermal
protection systems.
This editor gratefully acknowledges the contributions of the
Editorial Committee listed on page x, Miss Ruth F. Bryans,
Associate Series Editor, Miss Brenda Hio, Managing Editor of the
Series, and Dr. Martin Summerfield, Editor-in-Chief of the AIAA
Progress in Astronautics and Aeronautics series. The efforts of Dr.
Kenneth E. Harwell who organized the thermophysics sessions at the
AIAA 18th Aerospace Sciences Meeting, Dr. John E. Francis who
served as General Program Chairman of the AIAA 15th Ther-
mophysics Conference and chaired the AIAA Thermophysics
Technical Committee in 1979, and Mr. Jesse F. Keville who chaired
the AIAA Thermophysics Technical Committee in 1980 are also
greatly appreciated. Finally, the contributors to this volume are
thanked for their patience, cooperation, and care in the preparation
of their papers. , ,. _ ,.
AA1lfred L. Crosbie
March 1981
