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Approximate and exact numerical computation of supersonic flow over an airfoil

Published online by Cambridge University Press:  20 April 2006

Timothy S. Lewis  and
Lawrence Sirovich
Timothy S. Lewis
Affiliation:
Division of Applied Mathematics, Brown University, Providence, Rhode Island 02912
Lawrence Sirovich
Affiliation:
Division of Applied Mathematics, Brown University, Providence, Rhode Island 02912
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Abstract

An approximate solution is developed for two-dimensional, steady, inviscid supersonic flow over an airfoil. This approximation produces accurate results for a wide range of Mach numbers and airfoil thicknesses. It is used as the starting point for a rapidly convergent iterative numerical solution of the exact equations. A co-ordinate system consisting of the principal characteristics and streamlines is employed. Examples computed for a symmetric airfoil reveal several interesting features in the tail shock and the flow behind the airfoil.

Information

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 112 , November 1981 , pp. 265 - 282
Copyright
© 1981 Cambridge University Press

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