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Non-Equilibrium Flow in an Arcjet or a Shock Tube: Synthesis

  • J. Muylaert
  • B. Stoufflet
  • W. Goodrich
  • P. Fauchais
Conference paper

Abstract

The purpose of this test case is to obtain a better understanding of the non equilibrium flow field which exists in high enthalpy plasma tunnels. These tunnels are used to study the thermal protection system (TPS) for future spacecraft. To improve our understanding in the interpretation of measured data to enable proper extrapolation to flight it is mandatory to compute correctly these flow fields.

Keywords

Shock Tube Thermal Protection System Cone Half Angle Inlet Cross Section Computational Validation 
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 1991

Authors and Affiliations

  • J. Muylaert
    • 1
  • B. Stoufflet
    • 2
  • W. Goodrich
    • 3
  • P. Fauchais
    • 4
  1. 1.ESTECNoordwijkThe Netherlands
  2. 2.AMD-BASaint CloudFrance
  3. 3.AGARDNeuilly-Sur-SeineFrance
  4. 4.Univ. de LimogesLimogesFrance

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