Unified calculation of hypersonic flowfieid for a reentry vehicle

Toshiyuki Suzuki, Michiko Furudate, Keisuke Sawada

Research output: Contribution to conferencePaperpeer-review

Abstract

A unified CFD method is developed that integrates numerical methods for solving specific problems related to aerodynamic heating phenomena and ablative heatshield. Using this unified CFD code, trajectory-based analysis on the aerodynamic heating environment for the MUSES-C super-orbital reentry capsule is conducted. Converged solutions can be obtained by loosely coupling CFD code and CMA code within a few iterations. The results show that the wall surface temperature in the downstream region is significantly elevated by the effect of turbulence due to ablation product gas. Wall temperature as well as the recession rate at the stagnation point along the entry trajectory is found to duplicate well with the existing predictions.

Original languageEnglish
Publication statusPublished - 2001 Dec 1
Event39th Aerospace Sciences Meeting and Exhibit 2001 - Reno, NV, United States
Duration: 2001 Jan 82001 Jan 11

Other

Other39th Aerospace Sciences Meeting and Exhibit 2001
CountryUnited States
CityReno, NV
Period01/1/801/1/11

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

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