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The Calculation of Three-Dimensional Turbulent Boundary Layers: Part I: Flow over the Rear of 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

A method of calculation has been developed in which all terms in the momentum integral equations in the streamwise and cross-flow directions are taken into account so that no restriction to small cross-flows is imposed. The essential feature of the method is the use of an entrainment equation which enables the development of the streamwise form parameter to be calculated along with the streamwise and cross-flow momentum thicknesses. Mager’s quadratic expression is used to relate streamwise and cross-flow profiles. The method has been applied to the idealised case of an infinite swept wing with free-stream velocity over the forward part of the chord and a linear adverse velocity gradient over the rear. The position of separation, the directions of the surface streamlines and the development of streamwise and cross-flow profiles have been calculated for a series of angles of sweep and for adverse pressure gradients of varying severity.

Type
Research Article
Information
Aeronautical Quarterly , Volume 18 , Issue 1 , February 1967 , pp. 55 - 84
Copyright
Copyright © Royal Aeronautical Society. 1967

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