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A solution method for the three-dimensional compressible turbulent boundary-layer equations

Published online by Cambridge University Press:  04 July 2016

L. J. Johnston
L. J. Johnston*
Affiliation:
Aeronautics/Aerospace Department, von Karman Institute for Fluid Dynamics, B-1640 Rhode Saint Genèse-Belgium
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Summary

The development of a new calculation method for compressible 3D boundary layers is described. The method involves a finite-difference discretisation of the governing mean-flow equations. In particular, the differencing scheme used to discretise spanwise derivatives adapts automatically to the sign of the local crossflow within the boundary layer. A plane-by-plane solution procedure in the spanwise direction enables second-order accuracy to be maintained throughout the whole flowfield. A normal coordinate scaling with the local total momentum thickness removes most of the boundary layer growth in computational space. The Cebeci-Smith algebraic turbulence model is used for the initial validation of the calculation method. A simple modification to this model is tested, involving an explicit dependence of the outer eddy viscosity on the crossflow within the boundary layer. There results a significantly improved prediction of the NLR infinite swept wing flow experiment.

Type
Research Article
Information
The Aeronautical Journal , Volume 93 , Issue 924 , April 1989 , pp. 115 - 131
Copyright
Copyright © Royal Aeronautical Society 1989 

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