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Three-dimensional wings in hypersonic flow

Published online by Cambridge University Press:  29 March 2006

R. Hillier
R. Hillier
Affiliation:
Engineering Department, Cambridge University Present address: Central Electricity Research Laboratories, Leatherhead, Surrey.
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Abstract

Messiter's thin shock layer approximation for hypersonic wings is applied to several non-conical shapes. Two calculation methods are considered. One gives the exact solution for a particular three-dimensional geometry which possesses a conical planform and also a conical distribution of thickness superimposed upon a surface cambered in the chordwise direction. Agreement with experiment is good for all cases, including that where the wing is yawed. The other method is a more general approach whereby the solution is expressed as a correction to an already known conical flow. Such a technique is applicable to conical planforms with either attached or detached shocks but only to the non-conical planform for the region in the vicinity of the leading edge when the shock is attached.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 54 , Issue 2 , 25 July 1972 , pp. 305 - 337
Copyright
© 1972 Cambridge University Press

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