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LES of Shock Wave/Turbulent Boundary Layer Interaction

  • M. S. Loginov
  • N. A. Adams
  • A. A. Zheltovodov

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 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer-Verlag Berlin Heidelberg 2005

Authors and Affiliations

  • M. S. Loginov
    • 1
    • 2
  • N. A. Adams
    • 1
  • A. A. Zheltovodov
    • 2
  1. 1.Institute of Fluid MechanicsDresden University of TechnologyDresdenGermany
  2. 2.Institute of Theoretical and Applied MechanicsNovosibirskRussia

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