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- Thermal and inertial parameters of the flow field of a scramjet engine
- Hot Structure Flight Data of a Faceted Atmospheric Reentry Thermal Protection System
- Hypersonic and high-temperature gas dynamics - John David Anderson.pdf
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It is a sub-field of fluid dynamics and gas dynamics , and many aspects of aerodynamics theory are common to these fields. The term aerodynamics is often used synonymously with gas dynamics, the difference being that "gas dynamics" applies to the study of the motion of all gases, and is not limited to air. The formal study of aerodynamics began in the modern sense in the eighteenth century, although observations of fundamental concepts such as aerodynamic drag were recorded much earlier. Most of the early efforts in aerodynamics were directed toward achieving heavier-than-air flight , which was first demonstrated by Otto Lilienthal in Recent work in aerodynamics has focused on issues related to compressible flow , turbulence , and boundary layers and has become increasingly computational in nature.
Thermal and inertial parameters of the flow field of a scramjet engine
Book annotation not available for this title Hypersonic and High-Temperature Gas Dynamics.. Anderson, John David.. Publication Date:. Number of Pages:. Binding Type:MoreBook annotation not available for this title Binding Type:.
Hot Structure Flight Data of a Faceted Atmospheric Reentry Thermal Protection System
Zel'dovich Ya. Academic Press, Contents Editors' Foreword Preface to the English Edition Preface to the First Russian Edition Preface to the Second Russian Edition Condensed Contents of Volume I Shock wave structure in gases Physical and chemical kinetics in hydrodynamic processes Radiative phenomena in shock waves and in strong exploexplosions in air Thermal waves Shock waves in solids Some self-similar processes in gasdynamics Appendix: Some often used constants, relations between units, and formulas Author index Subject index. Anderson J. McGraw-Hill, Elsevier Science, , pages. This book deals with density, temperature, velocity and concentration fluctuations in fluids and fluid mixtures.
This page intentionally left blank, Hypersonic and High Temperature. Library of Congress Cataloging in Publication Data. Includes bibliographical references and index, ISBN 13 1 5 alk paper. America No part of this publication may be reproduced distributed or transmitted in any form or. Virginia Polytechnic Institute and State University.
Air-breathing hypersonic vehicles can be powered by scramjet supersonic combustion ramjet engines, whose inlet requires blunt leading edges in order to overcome the high heat fluxes that are inherent of hypersonic flights. Thus, this work has the purpose of evaluating, through detailed two-dimensional computational fluid dynamics analysis, the influence of the leading-edge bluntness and isolator height on the airflow of a scramjet intake. Three radii have been analyzed for the forebody and cowl leading edges: sharp, 0. The static temperature, pressure, and Mach number contour are part of the analysis, as well as the Stanton number and the adiabatic kinetic efficiency of the scramjet. It was evidenced that both leading-edge bluntness and isolator height performed great influence on the intake airflow structure.
Hypersonic and high-temperature gas dynamics - John David englishdistrictlifeline.org John Anderson is very well-qualified to write this book, first because of his broad.
Hypersonic and high-temperature gas dynamics - John David Anderson.pdf
Holman, Southern Methodist [nivers John r. New York St. Corrigan and Eleanor Castellano the production supervisor was Denise L. Puryear The cover was designed by Rafael hernandez R. All rights reserved.
The second sharp-edged flight experiment is a faceted suborbital reentry body that enables low-cost in-flight reentry research. Its faceted thermal protection system consisting of only flat radiation-cooled thermal protection panels is cost-efficient since it saves dies, manpower, and storage. The panel gaps are sealed by a ceramic seal. Part of the thermal protection system is an additional transpiration-cooling experiment in which nitrogen is exhausted through a permeable ceramic matrix composite to form a coolant film on the panel. The transient load at each panel location is derived from the trajectory by oblique shock equations and subsequent use of a heat balance for both cooled and uncooled structures.
Heat flux and pressure were measured on the internal walls of a scramjet engine at a hypersonic Mach number of 8 in a shock tunnel. Temperature-time history was recorded on model walls using fast-response thermocouples and the wall heat flux was deduced thereon from the temperature records. Pressure was measured at the same locations as that of heat flux using high-frequency pressure transducers.
This page intentionally left blank, Hypersonic and High Temperature.
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