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

In: High Performance Computing in Science and Engineering’ 04

Author

Listed:
  • Christian Stemmer

    (Technische Universität Dresden, Insitut für Strömungsmechanik)

  • Nikolaus A. Adams

    (Technische Universität Dresden, Insitut für Strömungsmechanik)

Abstract

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].

Suggested Citation

  • Christian Stemmer & Nikolaus A. Adams, 2005. "Investigation of Hypersonic Flat-plate Boundary-layer Transition by Direct Numerical Simulation," Springer Books, in: Egon Krause & Willi Jäger & Michael Resch (ed.), High Performance Computing in Science and Engineering’ 04, pages 155-162, Springer.
    • Handle: RePEc:spr:sprchp:978-3-540-26589-4_17
    DOI: 10.1007/3-540-26589-9_17
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