NASA NTRS · 19940010286
Response of a supersonic boundary layer to a compression corner
Abstract
On the basis of direct numerical simulations of rapidly compressed turbulence, Zeman and Coleman have developed a model to represent rapid directional compression contribution to the pressure dilatation term in the turbulent kinetic energy equation. The model has been implemented in the CFD code for simulation of supersonic compression corner flow with an extended separated region. The computational results have shown a significant improvement with respect to the baseline solution given by the standard k- epsilon turbulence model which does not contain any compressibility corrections.
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Vandromme, D., Zeman, O.. 1992-11-01. Response of a supersonic boundary layer to a compression corner. https://ntrs.nasa.gov/citations/19940010286
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