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The Pressure Distribution on a Wing with a Subsonic Leading Edge in the Presence of Anti-symmetric Body Shaping

Published online by Cambridge University Press:  07 June 2016

J. G. Jones
J. G. Jones*
Affiliation:
Royal Aircraft Establishment, Bedford
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Summary

The pressure distribution on the wing of a centrally mounted wingbody combination due to anti-symmetrical body shaping (with respect to the wing plane) can be calculated in the case where the wing leading edge is supersonic by using the fact that the upper and lower halves of the flow field are independent and that each half can be treated by quasi-cylinder theory. When the leading edge is subsonic the anti-symmetric body shaping produces flow round the leading edge. This paper is concerned with wing pressure distributions including the effect of this flow round the leading edge.

Type
Research Article
Information
Aeronautical Quarterly , Volume 11 , Issue 1 , February 1960 , pp. 51 - 70
Copyright
Copyright © Royal Aeronautical Society. 1960

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References

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