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Hypersonic Flow with Attached Shock Waves over Delta Wings

Published online by Cambridge University Press:  07 June 2016

B. A. Woods
B. A. Woods*
Affiliation:
School of Mathematics, University of Leeds*
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Summary

Hypersonic conical flows over delta wings are treated in the thin-shock-layer approximation due to Messiter. The equations are hyperbolic throughout, even in regions where the full equations are elliptic, and have not hitherto been solved for flows with attached shock waves. The concept of the simple wave has been used to construct a class of solutions for such flows; they contain discontinuities in flow variables and shock slope but, for the case of flow over a delta wing with lateral symmetry, agreement with results of numerical solutions of the full equations is good. The method is applied to plane delta wings at yaw, and to wings with anhedral and dihedral. For the flow at the tip of a rectangular wing, it is shown that two distinct solutions may be constructed.

Type
Research Article
Information
Aeronautical Quarterly , Volume 21 , Issue 4 , November 1970 , pp. 379 - 399
Copyright
Copyright © Royal Aeronautical Society. 1970

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References

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