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Numerical Simulation of Viscous Shock Layer Flows Fluid Mechanics and Its Applications

Y. P. Golovachov

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ISBN 10: 0792336267 / ISBN 13: 9780792336266
Published by Springer
New Condition: New Hardcover
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Hardcover. 348 pages. Dimensions: 9.2in. x 6.1in. x 0.9in.This book is the first to give a comprehensive presentation of the modern approach to numerical simulation of supersonic and hypersonic flows around bodies. In its use of the viscous gas dynamics equations throughout the computational domain, the main advantage of the approach presented is that it takes account of the important effects of rarefaction, viscous-inviscid interaction, separation, chemical and thermal non-equilibria, and radiation. A number of example calculations are given, demonstrating the application of the viscous shock layer models to a wide range of modern gas dynamics problems. Audience: Researchers into supersonic and hypersonic gas dynamics. Suitable for those already familiar with the fundamentals of gas dynamics, the physics of high-temperature gases and finite-difference numerical methods. Also suitable for graduate and postgraduate courses on computational gas dynamics and heat transfer. This item ships from multiple locations. Your book may arrive from Roseburg,OR, La Vergne,TN. Bookseller Inventory # 9780792336266

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Title: Numerical Simulation of Viscous Shock Layer ...

Publisher: Springer

Binding: Hardcover

Book Condition:New

Book Type: Hardcover

About this title


The book is concerned with mathematical modelling of supersonic and hyper­ sonic flows about bodies. Permanent interest in this topic is stimulated, first of all, by aviation and aerospace engineering. The designing of aircraft and space vehicles requires a more precise prediction of the aerodynamic and heat transfer characteristics. Together with broadening of the flight condition range, this makes it necessary to take into account a number of gas dynamic and physical effects caused by rarefaction, viscous-inviscid interaction, separation, various physical and chemical processes induced by gas heating in the intensive bow shock wave. The flow field around a body moving at supersonic speed can be divided into three parts, namely, shock layer, near wake including base flow, and far wake. The shock layer flow is bounded by the bow shock wave and the front and lat­ eral parts of the body surface. A conventional approach to calculation of shock layer flows consists in a successive solution of the inviscid gas and boundary layer equations. When the afore-mentioned effects become important, implementation of these models meets difficulties or even becomes impossible. In this case, one has to use a more general approach based on the viscous shock layer concept.

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