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The Effects on Wing Lift and Pitching Moment Due to the Fin of an Aircraft Flying at Supersonic Speeds

Published online by Cambridge University Press:  04 July 2016

L. B. Jones
L. B. Jones*
Affiliation:
University of Bradford
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Summary:

A simple expression is obtained for the lift induced upon a wing by the pressure field of the fin mounted upon the wing in supersonic flow. This expression holds for all fins with sharp edges provided that the wing trailing edge is normal to the free stream and that the Mach lines from the apex of the fin do not intersect the wing leading edge. If the fin has a blunt trailing edge the further restriction that the wing trailing edge is upstream of that of the fin is also required.

Results for the induced lift and pitching moment are presented for a delta fin with variations in size and position of the fin relative to the wing trailing edge.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 71 , Issue 674 , February 1967 , pp. 134 - 136
Copyright
Copyright © Royal Aeronautical Society 1967

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References

1.Ward, G. N.Linearised Theory of Steady High Speed Flow. Cambridge University Press.Google Scholar