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Shock-expansion theory and simple wave perturbation

Published online by Cambridge University Press:  28 March 2006

J. G. Jones
J. G. Jones
Affiliation:
Royal Aircraft Establishment, Bedford
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Abstract

The calculation by shock-expansion theory of supersonic aerofoil flow fields with varying entropy is simplified by assuming the flow behind the curved attached shock to be a small perturbation of a simple wave. A characteristic perturbation method is used.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 17 , Issue 4 , December 1963 , pp. 506 - 512
Copyright
© 1963 Cambridge University Press

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References

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