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

Christian Stemmer () and Nikolaus A. Adams
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Christian Stemmer: Technische Universität Dresden, Insitut für Strömungsmechanik
Nikolaus A. Adams: Technische Universität Dresden, Insitut für Strömungsmechanik

A chapter in High Performance Computing in Science and Engineering’ 04, 2005, pp 155-162 from Springer

Abstract: 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].

Keywords: Direct Numerical Simulation; Hypersonic Flow; Supersonic Boundary Layer; Qualitative Validation; Increase Computer Power (search for similar items in EconPapers)
Date: 2005
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Persistent link: https://EconPapers.repec.org/RePEc:spr:sprchp:978-3-540-26589-4_17

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DOI: 10.1007/3-540-26589-9_17

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