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The Design of Thin Finite Wings in Incompressible Flow

Published online by Cambridge University Press:  07 June 2016

G. J. Hancock
G. J. Hancock*
Affiliation:
Department of Mathematics, Sheffield University
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Summary

A method is developed for designing thin finite wings with prescribed lift distributions. Particular attention is given to wings which, at a certain optimum angle of incidence, have zero loading along the whole leading edge. It is suggested that such a wing will have a greater range of lift coefficient for low drag than other wings with the same plan form.

On the basis of the linearised theory a formula, relating the wing surface to the pressure distribution over the surface, is deduced which differs from the usual potential relationship by avoiding the difficulty of the non-uniform convergence with respect to the normal distance away from the wing surface singularities. The surface integral which is developed includes a regular singularity and a definite limiting process.

Type
Research Article
Information
Aeronautical Quarterly , Volume 5 , Issue 2 , July 1954 , pp. 119 - 130
Copyright
Copyright © Royal Aeronautical Society. 1954

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References

1. Goldstein, S. (1948). Low Drag and Suction Aerofoils. Journal of the Aeronautical Sciences, Vol. 15, April 1948.Google Scholar
2. Ursell, F. (1949). Notes on the Linear Theory of Incompressible Flow Around Symmetrical Swept-Back Wings at Zero Lift. The Aeronautical Quarterly, Vol. I, May 1949.Google Scholar