Investigation of Hypersonic Flat-plate Boundary-layer Transition by Direct Numerical Simulation

  • Christian Stemmer
  • Nikolaus A. Adams
Conference paper


Investigations on laminar-turbulent transition for high-speed flows at hypersonic Mach-numbers will be presented. Dissociation takes place above a temperature of T>2000K within the boundary layer, a temperature which is reached easily at Mach-numbers above M=5. Additional degrees of freedom for the energy must be taken into account by employing a vibrational energy equation. Chemical reactions take place which are modeled by a 5-species model proposed by Park [Par89]. Further details on the chemical modeling can be found in [Ste02, Ste03].

Controlled disturbances can be introduced by means of a disturbance strip at the wall which is also capable to model point source disturbances. Results will be shown for free-flight conditions at an altitude of H=50Km and at a speed of M=20. Experiments for qualitative validation of the results are available in [MM00].


Direct Numerical Simulation Hypersonic Flow Supersonic Boundary Layer Qualitative Validation Increase Computer Power 
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

  • Christian Stemmer
    • 1
  • Nikolaus A. Adams
    • 1
  1. 1.Insitut für StrömungsmechanikTechnische Universität DresdenDresdenGermany

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