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Supersonic flow and wing-body interference

Published online by Cambridge University Press:  26 February 2010

D. S. Jones
D. S. Jones
Affiliation:
The Department of Mathematics, Queen's College, Dundee.
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Summary

The velocity potential near the boundary of the disturbance is determined for steady supersonic flow past a simple body-and-wing model. It is found that the disturbance decays exponentially as it spreads round the body; the alteration caused by changing the radius of curvature is discussed. A universal formula for the potential away from the fuselage is also derived.

Information

Type
Research Article
Information
Mathematika , Volume 14 , Issue 1 , June 1967 , pp. 68 - 93
Copyright
Copyright © University College London 1967

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