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LES of Shock Wave/Turbulent Boundary Layer Interaction

In: High Performance Computing in Science and Engineering’ 04

Author

Listed:
  • M. S. Loginov

    (Dresden University of Technology, Institute of Fluid Mechanics
    Institute of Theoretical and Applied Mechanics)

  • N. A. Adams

    (Dresden University of Technology, Institute of Fluid Mechanics)

  • A. A. Zheltovodov

    (Institute of Theoretical and Applied Mechanics)

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.

Suggested Citation

  • M. S. Loginov & N. A. Adams & A. A. Zheltovodov, 2005. "LES of Shock Wave/Turbulent Boundary Layer Interaction," Springer Books, in: Egon Krause & Willi Jäger & Michael Resch (ed.), High Performance Computing in Science and Engineering’ 04, pages 177-188, Springer.
    • Handle: RePEc:spr:sprchp:978-3-540-26589-4_19
    DOI: 10.1007/3-540-26589-9_19
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