LES of Shock Wave/Turbulent Boundary Layer Interaction

M. S. Loginov (), N. A. Adams and A. A. Zheltovodov
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M. S. Loginov: Dresden University of Technology, Institute of Fluid Mechanics
N. A. Adams: Dresden University of Technology, Institute of Fluid Mechanics
A. A. Zheltovodov: Institute of Theoretical and Applied Mechanics

A chapter in High Performance Computing in Science and Engineering’ 04, 2005, pp 177-188 from Springer

Abstract: Abstract Shock-wave/turbulent-boundary-layer interaction compression-ramp flow is a canonical test configuration for statistical turbulence modeling. Extensive experimental data are available, whereas computational data focus mainly on Reynolds-averaged computations employing a wide range of turbulence models. In figure 1 basic flow features are sketched [Zhe91]. The undisturbed incoming turbulent boundary layer interacts with the shock wave, for suffi-ciently large deflection angles resulting in a separation region near the com-pression corner, and a A-shock system containing the separation region. Sub-sequently the disturbed boundary layer passes through the Prandtl-Meyer expansion near the decompression corner and finally relaxes towards a devel-oped zero-pressure-gradient boundary layer.

Keywords: Wall Pressure; Boundary Layer Interaction; Wall Pressure Fluctuation; Compression Ramp; Compression Corner (search for similar items in EconPapers)
Date: 2005
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DOI: 10.1007/3-540-26589-9_19

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