This high-level aerospace reference book will be useful for undergraduate and graduate students of engineering, applied mathematics and physics. The author provides solutions for three-dimensional compressible Navier-Stokes layer subsonic and supersonic flows.* Computational work and experimental results show the real-world application of computational results* Easy computation and visualization of inviscid and viscous aerodynamic characteristics of flying configurations* Includes a fully optimized and integrated design for a proposed supersonic transport aircraft
Front Cover; Dedication; Computation of Supersonic Flow over Flying Configurations; Copyright Page; Contents; About the Author; Preface; Acknowledgments; Chapter 1 Zonal, Spectral Solutions for the Three-Dimensional, Compressible Navier-Stokes Layer; 1.1 Introduction; 1.2 Three-dimensional, partial-differential equations of compressible Navier-Stokes layer (NSL); 1.3 The spectral variable and the spectral forms of the velocity's components and of the physical entities; 1.4 The first and second derivatives of the velocity's components 1.5 The implicit and explicit forms of the boundary conditions at the NSL's edge1.6 The dependence of the density function R versus the spectral velocity, inside the NSL; 1.7 Dependence of absolute temperature T versus the spectral velocity, inside the NSL; 1.8 The scalar forms of the NSL's impulse's partial-differential equations and their equivalent quadratical algebraic equations; 1.9 Determination of spectral coefficients of the velocity's components by solving an equivalent quadratical algebraic system, via the collocation method 1.10 An original iterative method to solve a quadratical algebraic system1.11 Conclusions; References; Chapter 2 Hyperbolical Potential Boundary Value Problems of the Axial Disturbance Velocities of Outer Flow, at NSL's Edge; 2.1 Introduction; 2.2 Basic equations; 2.3 Full-linearized partial-differential equations of the flow over flattened, flying configurations; 2.4 The characteristic hypersurfaces of the partial-differential equations of second order; 2.4.1 The classification of quasi-linear partial-differential equations of second order 2.4.2 The characteristic's condition and the characteristic hypersurface2.5 The linearized pressure coefficient C[sub(p)] on flying configurations; 2.6 The linearized boundary value problems for flying configurations, at moderate angles of attack α; 2.7 Definitions and properties of the thin and thick-symmetrical components of the thick, lifting flying configurations; 2.8 The disturbance regions produced by a moving point in subsonic and supersonic flow; 2.9 Disturbance regions and characteristic surfaces produced by triangular wings, in supersonic flow 2.10 Disturbance regions and characteristic surfaces produced by trapezoidal wings, in supersonic flow2.11 Disturbance regions and characteristic surfaces produced by rectangular wings, in supersonic flow; 2.12 The boundary value problems for the axial disturbance velocities on thin and thick-symmetrical wedged triangular wing components, in supersonic flow; 2.13 Conclusions; References; Chapter 3 Computation of Axial Disturbance Velocities on Wedged Wings, in Supersonic Flow, at NSL's Edge; 3.1 General considerations; 3.2 The conical flow of first order; 3.2.1 Definition of the conical flow 3.2.2 The Germain's complex plane
Description based upon print version of record. Includes bibliographical references and indexes.