Computation of Supersonic Flow over Flying Configurations

This book PDF is perfect for those who love Technology & Engineering genre, written by Adriana Nastase and published by Elsevier which was released on 07 July 2010 with total hardcover pages 410. You could read this book directly on your devices with pdf, epub and kindle format, check detail and related Computation of Supersonic Flow over Flying Configurations books below.

Computation of Supersonic Flow over Flying Configurations
Author : Adriana Nastase
File Size : 52,9 Mb
Publisher : Elsevier
Language : English
Release Date : 07 July 2010
ISBN : 008055699X
Pages : 410 pages
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Computation of Supersonic Flow over Flying Configurations by Adriana Nastase Book PDF Summary

Computation of Supersonic Flow over Flying Configurations is a high-level aerospace reference book that 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

Computation of Supersonic Flow over Flying Configurations

Computation of Supersonic Flow over Flying Configurations is a high-level aerospace reference book that 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

Get Book
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Supersonic Flow Computations for an Astovl Aircraft Configuration  Phase 2

A unified space/time marching method was used to solve the Euler and Reynolds-averaged Navier-Stokes equations for supersonic flow past an Advanced Short Take-off and Vertical Landing (ASTOVL) aircraft configuration. Lift and drag values obtained from the computations compare well with wind tunnel measurements. The entire calculation procedure is described

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"A calculative method is presented for determining separated, laminar, boundary-layer characteristics from in front of the separation point to the reattachment point under the influence of 'free interaction' between the main flow and the boundary layer. The analysis covers supersonic flow over two-dimensional and axisymmetric configurations with adiabatic or nonadiabatic

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Since the appearance of computers, numerical methods for discontinuous solutions of quasi-linear hyperbolic systems of partial differential equations have been among the most important research subjects in numerical analysis. The authors have developed a new difference method (named the singularity-separating method) for quasi-linear hyperbolic systems of partial differential equations. Its

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