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Uniform second-order solution for supersonic flow over delta wing using reverse-flow integral method

Published online by Cambridge University Press:  28 March 2006

Joseph H. Clarke  and
James Wallace
Joseph H. Clarke
Affiliation:
Division of Engineering, Brown University, Providence, Rhode Island
James Wallace
Affiliation:
Division of Engineering, Brown University, Providence, Rhode Island
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Abstract

The problem of supersonic flow over an inclined flat-plate delta wing with supersonic edges is solved to second order in incidence. This solution for surface pressure is uniform and fully analytic. The approach utilizes a reverse-flow integral method previously developed for second-order problems. This method is augmented by a number of techniques appropriate to its framework. The simplification over standard techniques achieved by using these reverse-flow methods is quite substantial and makes the problem tractable.

Reverse-flow procedures give a volume-surface integral relation that connects the second-order forward flow over the body of interest with the linearized reverse-flow over a related body. A singular integral equation is generated from the integral relation by introducing the edge sweep of the reverse-flow wing as a free parameter. An inversion is available which gives the second-order solution on the surface of the wing. The solution is then made uniformly valid using techniques previously developed.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 18 , Issue 2 , February 1964 , pp. 225 - 238
Copyright
© 1964 Cambridge University Press

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