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Lifting Wings with Mixed (Subsonic-Supersonic) Leading Edges

Published online by Cambridge University Press:  07 June 2016

J. H. B. Smith ,
D. Pierce  and
Patricia J. Rossiter
J. H. B. Smith
Affiliation:
Royal Aircraft Establishment, Farnborough
D. Pierce
Affiliation:
Royal Aircraft Establishment, Farnborough
Patricia J. Rossiter
Affiliation:
Royal Aircraft Establishment, Farnborough
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Summary

The linearised theory of supersonic flow is applied to a plane wing with a pointed apex whose leading edge is subsonic near the apex but supersonic further outboard. The change in character of the leading edge may occur either where the edge is kinked or at a point where its slope is continuous. In each case, the theoretical pressure field due to incidence is found to be singular along the downstream, outward-going Mach line through the point at which the edge changes character. The form of the singularity is different for the two cases, and somewhat unexpected. Measurements of the pressure on a plane wing with a curved, mixed leading edge showed no abrupt variation near the Mach line on which the singular behaviour was predicted.

Type
Research Article
Information
Aeronautical Quarterly , Volume 21 , Issue 4 , November 1970 , pp. 355 - 367
Copyright
Copyright © Royal Aeronautical Society. 1970

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References

1. Cohen, D. and Friedman, M. D. Theoretical investigation of the supersonic lift and drag of thin, sweptback wings with increased sweep near the root. NACA TN 2959, 1953.Google Scholar
2. Smith, J. H. B., Pierce, D. and Rossiter, P. J. Lifting wings with mixed (subsonic-supersonic) leading edges. RAE Technical Report 68 210, ARC 31 127, 1968.Google Scholar