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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

Courant R. & Friedrichs, K. O. 1948 Supersonic Flow and Shock Waves. New York: Interscience.
Eggers, A. J., Syvertson, C. A. & Kraus, S. 1953 A study of inviscid flow about airfoils at high supersonic speeds. NACA Rep. no. 1123.Google Scholar
Epstein, P. S. 1931 On the air resistance of projectiles. Proc. Nat. Acad. Sci., 17, 160–161.Google Scholar
Friedrichs, K. O. 1948 Formation and decay of shock waves. Comm. Pure Appl. Math., 1, 211–245.Google Scholar
Mahoney, J. J. 1955 A critique of shock-expansion theory. J. Aero. Sci. 22, 676–680, 720.Google Scholar
Mahoney, J. J. & Skeat, P. R. 1955 The flow around a supersonic aerofoil. Austr. Dept. of Supply Note ARL/A. 147.Google Scholar
Meyer, R. E. 1956 On supersonic flow being a curved shock. Quart. Appl. Math., 14, 433–436.Google Scholar
Waldman, G. D. & Probstein, R. F. 1961 An analytic extension of the shock-expansion method. J. Aero sp. Sci. 28, 119–132.Google Scholar