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The prediction of separated flow using a viscous-inviscid interaction method

Published online by Cambridge University Press:  04 July 2016

B.R. Williams
B.R. Williams*
Affiliation:
Aerodynamics Department, Royal Aircraft Establishment, Farnborough
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Summary

The separation of boundary-layer flow from a wing or in a diffuser usually defines the limit of efficient operation, so it is important that the onset and development of separated flow can be predicted. The calculation of the interaction of the shear layout close to an aerofoil with the external inviscid flow has offered an attractive alternative to solving the Reynoldsaveraged Navier Stokes equations for attached flow: the interaction method is much faster. In this paper it is shown how the interaction approach can be extended for use with separated flows and the development of a practical method is described. The calculation of the shear layer through the singularity at separation is accomplished by using an inverse mode. Beyond separation the empirical definition of a new family of velocity profiles allows an integral calculation of the shear layer to proceed up to the reattachment. The solutions for the shear layer close to the aerofoil are matched to the external inviscid flow by a ‘semi-inverse’ method. A careful examination of the stability of this method leads to rapid convergence for separated and attached flows. As an illustration the stall and post stall behaviour of a twodimensional aerofoil is predicted and compared with experimental results.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 89 , Issue 885 , May 1985 , pp. 185 - 197
Copyright
Copyright © Royal Aeronautical Society 1985 

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