Reynolds Stress Modeling for Hypersonic Flows

  • A. Bosco
  • B. Reinartz
  • S. Müller
  • L. Brown
  • R. Boyce
Part of the Springer Proceedings in Physics book series (SPPHY, volume 141)

Abstract

Despite the enormous increase in computational capabilities and use of computational fluid dynamics as a design tool in the aircraft industry, the correct prediction of complex hypersonic turbulent flows involving shock wave boundary layer interaction (SWBLI) is still a challenge [1]. Well assessed turbulence models that are known to perform properly at lower speed, cannot be used in hypervelocity flows without a proper validation. In this paper the use of a differential Reynolds Stress Model for the prediction of SWBLI on a compression corner is presented and the results are discussed for attached and separated boundary layers.

Keywords

Reynolds Stress Hypersonic Flow Reynolds Stress Model Eddy Viscosity Model Separate Boundary Layer 
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 2012

Authors and Affiliations

  • A. Bosco
    • 1
  • B. Reinartz
    • 1
  • S. Müller
    • 1
  • L. Brown
    • 2
  • R. Boyce
    • 2
  1. 1.RWTH AachenAachenGermany
  2. 2.University of QueenslandSt LuciaAustralia

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