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Simulation of blunt-fin-induced shock-wave and turbulent boundary-layer interaction

Published online by Cambridge University Press:  20 April 2006

Ching-Mao Hung  and
Pieter G. Buning
Ching-Mao Hung
Affiliation:
Computational Fluid Dynamics Branch, NASA Ames Research Center, Moffett Field, California
Pieter G. Buning
Affiliation:
Computational Fluid Dynamics Branch, NASA Ames Research Center, Moffett Field, California
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Abstract

The Reynolds-averaged Navier–Stokes equations are solved numerically for supersonic flow over a blunt fin mounted on a flat plate. The fin shock causes the boundary layer to separate, which results in a complicated, three-dimensional shock-wave and boundary-layer interaction. The computed results are in good agreement with the mean static pressure measured on the fin and the flat plate. The main features, such as peak pressure on the fin leading edge and a double peak on the plate, are predicted well. The role of the horseshoe vortex is discussed. This vortex leads to the development of high-speed flow and, hence, low-pressure regions on the fin and the plate. Different thicknesses of the incoming boundary layer have been studied. Varying the thicknesses by an order of magnitude shows that the size of the horseshoe vortex and, therefore, the spatial extent of the interaction are dominated by inviscid flow and only weakly dependent on the Reynolds number. Coloured graphics are used to show details of the interaction flow field.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 154 , May 1985 , pp. 163 - 185
Copyright
© 1985 Cambridge University Press

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