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Strongly Coupled Computation of Material Response and Nonequilibrium Flow for Hypersonic Ablation
Journal of Spacecraft and Rockets (2015)
  • Alexandre Martin, University of Kentucky
  • Iain D. Boyd

The steps necessary to achieve the strong coupling between a flowfield solver and a material response solver are presented. This type of coupling is required to accurately capture the complex aerothermodynamic physics occurring during hypersonic atmospheric entries. A blowing boundary condition for the flowfield solver is proposed. This allows the ablating gas calculated by the material response solver to be correctly injected in the boundary layer. A moving mesh algorithm for the flowfield solver that implicitly enforces the geometric conservation law is presented. Using that capability, a mesh movement procedure for surface recession and for accurate shock capturing is proposed. The entire technique is tested using a material response solver with surface ablation and pyrolysis coupled to a hypersonic solver for weakly ionized flows in thermochemical nonequilibrium. Results using the reentry trajectory of the IRV-2 test vehicle are presented, showing that the surface heat fluxes remain accurate as the vehicle geometry and freestream conditions change.

  • Strongly Coupled Computation,
  • Material Response,
  • Nonequilibrium Flow,
  • Hypersonic Ablation,
  • Pyrolysis,
  • Thermochemical nonequilibrium,
  • Heat fluxes
Publication Date
Citation Information
Alexandre Martin and Iain D. Boyd. "Strongly Coupled Computation of Material Response and Nonequilibrium Flow for Hypersonic Ablation" Journal of Spacecraft and Rockets Vol. 52 Iss. 1 (2015)
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