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Theory of an oscillating supersonic aerofoil

Published online by Cambridge University Press:  07 June 2016

Geoffrey L. Sewell
Geoffrey L. Sewell*
Affiliation:
King’s College, London
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Extract

In the previous linearised theories of steady supersonic flow past a slender oscillating aerofoil, the shock line at the nose has been assumed to be a straight, stationary one, so that no vorticity is produced on passing through it. In the present treatment, the possibility that the shock may be both curved and moving is taken into account, but the result is exactly the same as that obtained by the previous treatments (e.g. Temple and Jahn).

Type
Research Article
Information
Aeronautical Quarterly , Volume 2 , Issue 1 , May 1950 , pp. 34 - 38
Copyright
Copyright © Royal Aeronautical Society. 1950

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References

1. Temple, G., and Jahn, H. A. (1945). Flutter at Supersonic Speeds. R. & M. 2140, April 1945.Google Scholar
2. Carrier, G. F. (1949). On the Stability of Supersonic Flow past a Wedge. Quarterly of Applied Mathematics, Vol. VI, No. 4, January 1949.Google Scholar