An Introduction To Compressible Flow
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An Introduction to Compressible Flow
An Introduction to Compressible Flow is a concise, yet comprehensive treatment of one_dimensional compressible flow designed to provide mechanical and aerospace engineering students with the background they need for aerodynamics and turbomachinery courses. This book covers isentropic flow, normal shock waves, oblique shock waves, and Prandtl_Meyer flow and their applications. The first chapter reviews the physics of air, control volume analysis and provides a review of thermodynamics. Most textbooks provide very concise treatments of compressible flow- this text will supplement that material, which is often too concise to provide students with the background they need. This book also supports practicing engineers who have never developed a mastery of issues related to one_dimensional compressible flow or who need to review this material at some point in their careers. The appendices provide the tables and charts commonly associated with this material. One new addition is an oblique shock table, which tabulates the oblique shock angle for the weak shock solution as a function of Mach number and deflection angle. The book includes examples of problem solutions, and each chapter has a list of problems to enable students to apply their understanding.
An Introduction to Compressible Flow
An Introduction to Compressible Flow, Second Edition covers the material typical of a single-semester course in compressible flow. The book begins with a brief review of thermodynamics and control volume fluid dynamics, then proceeds to cover isentropic flow, normal shock waves, shock tubes, oblique shock waves, Prandtl-Meyer expansion fans, Fanno-line flow, Rayleigh-line flow, and conical shock waves. The book includes a chapter on linearized flow following chapters on oblique shocks and Prandtl-Meyer flows to appropriately ground students in this approximate method. It includes detailed appendices to support problem solutions and covers new oblique shock tables, which allow for quick and accurate solutions of flows with concave corners. The book is intended for senior undergraduate engineering students studying thermal-fluids and practicing engineers in the areas of aerospace or energy conversion. This book is also useful in providing supplemental coverage of compressible flow material in gas turbine and aerodynamics courses.
Compressible Fluid Flow and Systems of Conservation Laws in Several Space Variables
Author: A. Majda
language: en
Publisher: Springer Science & Business Media
Release Date: 2012-12-06
Conservation laws arise from the modeling of physical processes through the following three steps: 1) The appropriate physical balance laws are derived for m-phy- t cal quantities, ul""'~ with u = (ul' ... ,u ) and u(x,t) defined m for x = (xl""'~) E RN (N = 1,2, or 3), t > 0 and with the values m u(x,t) lying in an open subset, G, of R , the state space. The state space G arises because physical quantities such as the density or total energy should always be positive; thus the values of u are often con strained to an open set G. 2) The flux functions appearing in these balance laws are idealized through prescribed nonlinear functions, F.(u), mapping G into J j = 1, ..• ,N while source terms are defined by S(u,x,t) with S a given smooth function of these arguments with values in Rm. In parti- lar, the detailed microscopic effects of diffusion and dissipation are ignored. 3) A generalized version of the principle of virtual work is applied (see Antman [1]). The formal result of applying the three steps (1)-(3) is that the m physical quantities u define a weak solution of an m x m system of conservation laws, o I + N(Wt'u + r W ·F.(u) + W·S(u,x,t))dxdt (1.1) R xR j=l Xj J for all W E C~(RN x R+), W(x,t) E Rm.