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A new method for treating supersonic flow past nearly plane wings

Published online by Cambridge University Press:  28 March 2006

Myrna Lewin  and
Robert A. Schmeltzer
Myrna Lewin
Affiliation:
North American Aviation, Los Angeles Division, Los Angeles, California Present address: Courant Institute of mathematical Sciences, New York University.
Robert A. Schmeltzer
Affiliation:
North American Aviation, Los Angeles Division, Los Angeles, California Present address: Bell Telephone Laboratories, Holmdel, New Jersey.
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Abstract

Function-theoretic techniques are used for determining the supersonic flow past a wing of infinite length having a straight leading edge. The problem is reduced to a set of dual integral equations which are solved by function - theoretic methods. This approach is shown to be useful for treating more general - type leading edges yielding closed - form solutions which heretofore have been unobtainable. The general solutions obtained here are shown to be in complete agreement with previous solutions for the flow at large distances downstream on the aerofoil. For a wing of infinite span, the solution reduces to the well - known perturbation potential for a distribution of sources in a horizontal plane.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 17 , Issue 2 , October 1963 , pp. 305 - 313
Copyright
© 1963 Cambridge University Press

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References

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