Computation of supersonic flow over flying configurations
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 r...
| Autor principal: | |
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| Formato: | Libro electrónico |
| Idioma: | Inglés |
| Publicado: |
Amsterdam ; Boston :
Elsevier
2008.
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| Edición: | 1st ed |
| Materias: | |
| Ver en Biblioteca Universitat Ramon Llull: | https://discovery.url.edu/permalink/34CSUC_URL/1im36ta/alma991009627543306719 |
Tabla de Contenidos:
- 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
