Numerical Calculation of the Transonic Flow Past a Swept Wing (Classic Reprint) - Softcover

Antony Jameson

9781332956432: Numerical Calculation of the Transonic Flow Past a Swept Wing (Classic Reprint)

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ISBN 10: 1332956432 ISBN 13: 9781332956432

Publisher: Forgotten Books, 2018

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Predict transonic flow over swept wings with a robust numerical method. This edition explains how the full potential equation is solved on complex wing geometries.

This book presents a practical approach to predicting inviscid, transonic flows around swept wings. It describes a finite-difference framework and a rotated difference scheme, focusing on how geometry and coordinate choices affect accuracy and stability in simulations.

Learn how coordinate transformations and conformal mappings simplify boundary conditions on wing surfaces.
Understand how nonconservative and conservative formulations influence shock behavior and modeling of shock-boundary layer interactions.
See how vortex sheets and trailing-edge dynamics are represented in a numerical setting.
Explore the setup of a rectangular computational domain and the handling of far-field and near-edge regions with stretching transformations.

Ideal for readers of computational aerodynamics and engineers seeking a clear view of translating theory into a working simulation for transonic wing flows.

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Publisher: Forgotten Books
Publication date: 2018
Language: English
ISBN 10: 1332956432
ISBN 13: 9781332956432
Binding: Paperback
Number of pages: 107

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Numerical Calculation of the Transonic Flow Past a Swept Wing (Classic Reprint)

Antony Jameson, D. A. Caughey

Published by Forgotten Books, 2018

ISBN 10: 1332956432 ISBN 13: 9781332956432

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Seller: Forgotten Books, London, United Kingdom

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Paperback. Condition: New. Print on Demand. This book analyzes the transonic potential flow past a swept wing, extending the computational method of Jameson for an airfoil to the three-dimensional case. The flow is analyzed in coordinates nearly conformally mapped from the physical space in planes parallel to the symmetry plane, reducing the wing surface to a portion of one boundary of the computational grid. The finite difference approximation is in conservation form, which introduces substantial errors in the treatment of shocks without using a shock fitting scheme or else a difference scheme in conservation form. To assure the correct shock jump relations the author uses a rotated difference scheme, and the difference equations are solved by relaxation. The method is capable of treating wings of arbitrary planform and dihedral, although approximations in treating the tips and vortex sheet make its accuracy suspect for wings of small aspect ratio. This book is a reproduction of an important historical work, digitally reconstructed using state-of-the-art technology to preserve the original format. In rare cases, an imperfection in the original, such as a blemish or missing page, may be replicated in the book. print-on-demand item. Seller Inventory # 9781332956432_0

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