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Shock-shock interaction on a slender supersonic cone

Published online by Cambridge University Press:  28 March 2006

Victor D. Blankenship
Victor D. Blankenship
Affiliation:
Office of Research, Aerospace Corporation, San Bernardino, California
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Abstract

The transient pressure field produced behind a plane shock wave of arbitrary strength, which encounters a slender supersonic cone head on, is theoretically predicted. The analysis is restricted to small cone angles (in order that Mach-reflexion will occur at the surface) and to inviscid flow.

A conical-flow technique is utilized to transform the small-perturbation equations of time-dependent rotational motion of the fluid behind the deflected plane shock into time-independent equations. From these equations, a boundary-value problem for pressure alone, in the Mach-reflexion region, is derived which is solved numerically. Results for the small perturbation pressure field of the cone are contrasted with Smyrl's (1963) results, which hold for a moving wedge, for a range of values of cone and plane shock speeds.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 22 , Issue 3 , July 1965 , pp. 599 - 615
Copyright
© 1965 Cambridge University Press

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