Re-Entry Aerodynamics

152 Pages·1988·5.27 MB·English

by  Hankey M. L.

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Re-Entry Aerodynamics
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arc. Wilbur L. Hankey
http:// Wright State University
3 | Dayton, Ohio
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R AIAA EDUCATION SERIES
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Published by
American Institute of Aeronautics and Astronautics Inc.,
370 L'Enfant Promenade SW, Washington, DC 20024
Text Published In the AIAA Education Series
Re-Entry Vehicle Dynamics
Frank J. Regan, 1984
Aerothermodynamics of Gas Turbine and Rocket Propulsion
Gordon C. Gates, 1984
Aerothermodynamics of Aircraft Engine Components
Gordon C. Gates, Editor, 1985
2 Fundamentals of Aircraft Combat Survivability Analysis and Design
4
23 Robert E. Ball, 1985
6
4.8 Intake Aerodynamics
14/ J. Seddon and E. L. Goldsmith, 1985
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0.2 Composite Materials for Aircraft Structures
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OI: Brian C. Hoskin and Alan A. Baker, Editors, 1986
D Gasdynamics: Theory and Applications
org | George Emanuel, 1986
aa. Aircraft Engine Design
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p:// An Introduction to The Mathematics and Methods of Astrodynamics
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D o Aerothermodynamics of Gas Turbine and Rocket Propulsion, Revised and Enlarged
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A Gordon C. Gates, 1988
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Y American Institute of Aeronautics and Astronautics, Inc.
SIT Washington, DC
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NI Library of Congress Cataloging in Publication Data
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d b Hankey, Wilbur, L.
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ad Re-entry aerodynamics.
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Includes index.
I. Space vehicles-Atmospheric entry. I. Title.
II. Series.
TL1060.H36 1988 629.4'152 87-37369
ISBN 0-930403-33-9
Copyright © 1988 by the American Institute of Aeronautics and Astronautics, Inc. All rights
reserved. Printed in the United States of America. No part of this publication may be
reproduced, distributed, or transmitted, in any form or by any means, or stored in a data base
or retrieval system, without the prior written permission of the publisher.
FOREWORD
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8 Wllbur L. Hankey's text, Re-Entry Aerodynamics, which grew from
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4/ his lectures in a graduate-level course on hypersonics at the Air
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0.2 Force Institute of Technology, summarizes current theories for the
OI: 1 analysis of aerodynamic flow about bodies or vehicles re-entering the
D Earth's atmosphere. It represents a welcome addition to the AIAA
g | Education Series because of the renewed interest in extending the
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aa. sustained flight regime well into the hypersonic range—as in the
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c. National Aerospace Plane (NASP) project. Hankey's book is a com-
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p:// panion volume to the first text published in the AIAA Education
htt Series, Re-Entry Vehicle Dynamics by Frank J. Began.
13 | Dr. Hankey's first chapter treats the kinetic theory of gases as an
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0, 2 introduction to the transport phenomena in re-entry, including three
e 1 flight regimes: continuum flow, slip flow, and free molecule flow. His
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n Ju second chapter discusses some of the fundamental concepts for
o trajectory analysis of re-entering vehicles. The third chapter intro-
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U means of alleviating its effects.
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OF Dr. Hankey has written a textbook that provides the overall back-
Y ground for analysis of aerodynamic flow of re-entering bodies and
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SI vehicles throughout the whole range of flow regimes. The text reflects
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V his extensive knowledge of the field and his many years of experience
UNI as a senior research scientist in his previous positions with the
by Aerospace Research Laboratories and the Air Force Flight Dynamics
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e Laboratory at Wright-Patterson Air Force Base, Ohio.
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Do J. S. PRZEMIENIECKI
Editor-in-Chief
AIAA Education Series
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TABLE OF
CONTENTS
vii Preface
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4 1 Nomenclature
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4.
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2 1.1 Introduction
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g | 1.4 Dimensional Analysis
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p://ar Problems
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3 | 23 Chapter 2. Flight Mechanics
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e 1 2.2 Range Modulation
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o Problems
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E 3.1 Governing Equations
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OF 3.3 Hypersonic Aerodynamic Characteristics
TY 3.4 Hypersonic vs Subsonic Aerodynamics
RSI Problems
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4.5 Fay-Riddell Solution
4.6 Interference Heating
4.7 Ablation
4.8 Hot-Gas Radiation
4.9 Combined Forms of Heating
Problems
143 Index
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PREFACE
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OI: 1 ties offered courses in hypersonics, rarefied gasdynamics, super-
D aerodynamics, celestial mechanics, and aerothermochemistry.
g | Government, industry, and universities developed hypersonic facili-
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a. ties. Most existing hypersonic textbooks were written shortly after-
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c.ai wards, during the early '60s, including some of the chapters of this
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htt nation became disenchanted with aerospace. Projects were canceled,
3 | fiscal budgets slashed, wind-tunnel facilities closed down, engineers
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e 1 not to enter engineering, and enrollments plummeted.
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n Ju But in the '80s, with the Shuttle on line, a space station in the offing,
o a surge of funding for the Strategic Defense Initiative (SDI) and, more
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Y of the Education Series, John S. Przemieniecki, prompted the rewrit-
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VE nature, focuses attention on the critical aspects of re-entry, such as
UNI flight mechanics from low speed to orbital velocities, stability at high
by speeds, hypersonic aerodynamics, and re-entry heating.
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WILBUR L. HANKEY
Wright State University
Dayton, Ohio
2 NOMENCLATURE
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0.2 a = speed of sound, ft/s
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D A = area, ft2
org | Cf = skin-friction factor
aiaa. CD = drag coefficient
c. C = lift coefficient
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13 | v (air 4290), ft2/s2-°R
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0, 2 CP = specific heat at constant pressure
e 1 (air 6006), ft2/s2-°R
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n Ju Cl = constant
D o D = drag, Ib
AN D = diffusion coefficient, ft2/s
SL e = specific internal energy, ft2/s2, = C T+ V2/2
N V
E E = total energy, ft • lb/= frequency, s"1
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Q F = force, Ib
OF g = acceleration on gravity, ft/s2
TY h = altitude, ft
RSI h = specific enthalpy, ft2/s2
VE H = total enthalpy, ft2/s2, =h+ V2/2
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U i, y, k = Cartesian unit vectors
by / = conversion factor 778, ft • Ib/Btu
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L = length, ft
Le = Lewis number
m = mass, slug
m = mass flow rate, slug/s
M = total mass, slug
M = Mach number
Jf = molecular weight
N = total number
Nu = Nusselts number
p = pressure, lb/ft2
1
2 NOMENCLATURE
P = period, s
P = stress tensor, lb/ft2
Pr = Prandtl number
q = heating rate/unit area, Btu/ft2 • s
Q = heat energy, Btu
R = gas constant (air 1716), ft2/s2 - °R
R = radius, ft
Re = Reynolds number
S = reference area, ft2
St = Stanton number
42 t = time, s
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4/4. w, F, w = Cartesian velocity components, ft/s
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10. V = volume, ft3
OI: W = weight, Ib
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g | x, y, z = Cartesian coordinates, ft
a.or a = angle of attack, rad
aia a = atmospheric altitude factor, ft"1
arc. /? = ballistic coefficient, slug/ft3
http:// Y = specific heat ratio (air 1.4), = Cp/Cv
3 | Y = flight path angle, rad
1
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10, e = emissivity
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n r, 0 = polar coordinates, ft • rad
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ND X = second viscosity coefficient, = - f ju, Ib • s/ft2
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L A = sweep angle, rad
S
N ju, = viscosity, Ib • s/ft2
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UE v = kinematic viscosity, = ju/p, ft2/s
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F p = density, slug/ft3
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SIT a = Stephan-Boltzmann constant, = 0.481 X 10~12, Btu/ft2 • s • °R4
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E oj = normal stress, lb/ft2
V f
NI r = shear stress, lb/ft2
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