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Note on the Forces that Act near the Centre and the Tips of a Swept-Back Wing

Published online by Cambridge University Press:  07 June 2016

D. G. Hurley
D. G. Hurley*
Affiliation:
Aeronautical Research Laboratories, Melbourne
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Summary

The momentum equation is used to calculate the drag that acts near the tip of a semi-infinite swept-forward wing of constant chord that is at zero incidence to a uniform stream of incompressible, inviscid fluid. The drag is given as a function of wing section and angle of sweep and is shown to be unaffected by shaping the tip. The results may be used to calculate the drag that acts near die centre and the thrusts that act near the tips of a swept-back wing, provided that its aspect ratio is sufficiently great for the regions where the different forces act to be separated. Some results due to Neumark and to Küchemann and Weber suggest that this will be so provided that the aspect ratio is greater than about two. The results are combined with some due to these authors to estimate the spanwise extent of the forces. It is found that this extent decreases as the angle of sweep is increased and that it depends quite markedly on the wing section.

Type
Research Article
Information
Aeronautical Quarterly , Volume 10 , Issue 2 , May 1959 , pp. 127 - 144
Copyright
Copyright © Royal Aeronautical Society. 1958

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References

1. Neumark, S. Critical Mach Numbers for Swept-Back Wings. Aeronautical Quarterly, Vol. II, pp. 85–110, August 1950.Google Scholar
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