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The Calculation of Three-Dimensional Turbulent Boundary Layers: Part II: Attachment-Line Flow on an Infinite Swept Wing

Published online by Cambridge University Press:  07 June 2016

N. A. Cumpsty  and
M. R. Head
N. A. Cumpsty
Affiliation:
Cambridge University Engineering Laboratory
M. R. Head
Affiliation:
Cambridge University Engineering Laboratory
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Summary

An earlier paper described a method of calculating the turbulent boundary layer flow over the rear of an infinite swept wing. It made use of an entrainment equation and momentum integral equations in streamwise and cross-flow directions, together with several auxiliary assumptions. Here the method is adapted to the calculation of the turbulent boundary layer flow along the attachment line of an infinite swept wing. In this case the cross-flow momentum integral equation reduces to the identity 0 = 0 and must be replaced by its differentiated form. Two alternative approaches are also adopted and give very similar results, in good agreement with the limited experimental data available. It is found that results can be expressed as functions of a single parameter C*, which is evidently the criterion of similarity for attachment-line flows.

Type
Research Article
Information
Aeronautical Quarterly , Volume 18 , Issue 2 , May 1967 , pp. 150 - 164
Copyright
Copyright © Royal Aeronautical Society. 1967

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References

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