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The Effects of Yaw on Conical Wings at High Supersonic Speeds

Published online by Cambridge University Press:  07 June 2016

R. Hillier
R. Hillier*
Affiliation:
Cambridge University, Engineering Department
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Summary

In recent papers Squire has presented results for the shock shape and pressure distribution on the lower surface of unyawed, lifing, conical bodies with sharp leading edges. The work, a development of Messiter’s first-order correction to Newtonian theory, was successfully applied to wings of diamond and caret section. This paper shows how the method may be used to include the effects of yaw. Results are presented here for the flat wing and some biconvex sections. Comparisons are made with experiment for both the flat and biconvex wings and agreement is shown to be good.

Type
Research Article
Information
Aeronautical Quarterly , Volume 21 , Issue 3 , August 1970 , pp. 199 - 210
Copyright
Copyright © Royal Aeronautical Society. 1970

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References

1. Messiter, A. F. Lift of slender delta wings according to Newtonian theory. AIAA Journal, Vol. 1, p. 794, 1963.Google Scholar
2. Squire, L. C. Calculated pressure distributions and shock shapes on thick conical wings at high supersonic speeds. Aeronautical Quarterly, Vol. XVIII, p. 185, 1967.CrossRefGoogle Scholar
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