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The Effect of the Boundary Layer on the Lift of Finite Wings

Published online by Cambridge University Press:  07 June 2016

L. C. Squire
L. C. Squire*
Affiliation:
Department of Aeronautical Engineering, The Queen's University of Belfast
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Summary

The vorticity shed behind a finite wing has been studied and a condition found for steady circulation. This condition is then combined with three-dimensional boundary layer theory to find the lift of a finite wing. An example shows that on a thin ellipsoid of aspect ratio 6·37 the lift as found by the present method is 2 per cent lower than the lift obtained using a sectional boundary layer approach.

Type
Research Article
Information
Aeronautical Quarterly , Volume 14 , Issue 3 , August 1963 , pp. 241 - 253
Copyright
Copyright © Royal Aeronautical Society. 1963

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References

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