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Boundary Layers over Infinite Yawed Wings

Published online by Cambridge University Press:  07 June 2016

J. C. Cooke
J. C. Cooke*
Affiliation:
Royal Aircraft Establishment, Farnborough
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Summary

A method of calculating turbulent boundary layers on infinite yawed wings is given, making use of a method of calculating turbulent boundary layers due to Spence and of an analogy between three-dimensional and axi-symmetric boundary layers. It is also shown that the displacement thickness is equal to that computed using chordwise components and that the streamwise momentum thickness is approximately equal to the chordwise momentum thickness. Shock-free flow and small boundary layer cross-flow are assumed.

Information

Type
Research Article
Information
Aeronautical Quarterly , Volume 11 , Issue 4 , November 1960, pp. 333 - 347
Copyright
Copyright © Royal Aeronautical Society. 1960

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References

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