Unified calculation of hypersonic flowfield for a reentry vehicle

Toshiyuki Suzuki; Michiko Furudate; Keisuke Sawada

doi:10.2514/2.6656

Unified calculation of hypersonic flowfield for a reentry vehicle

Toshiyuki Suzuki, Michiko Furudate, Keisuke Sawada

ENG - Aerospace Engineering

Research output: Contribution to journal › Article › peer-review

41 Citations (Scopus)

Abstract

A unified computational fluid dynamics (CFD) method is developed that integrates numerical methods for solving specific problems related to aerodynamic heating phenomena and ablative heatshield. With the use of this unified CFD code, trajectory-based analysis on the aerodynamic heating environment for the MUSES-C superorbital reentry capsule is conducted. Converged solutions can be obtained by loosely coupling the CFD code and the charring materials ablation 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 the existing predictions.

Original language	English
Pages (from-to)	94-100
Number of pages	7
Journal	Journal of thermophysics and heat transfer
Volume	16
Issue number	1
DOIs	https://doi.org/10.2514/2.6656
Publication status	Published - 2002

ASJC Scopus subject areas

Condensed Matter Physics
Aerospace Engineering
Mechanical Engineering
Fluid Flow and Transfer Processes
Space and Planetary Science

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AU - Furudate, Michiko

AU - Sawada, Keisuke

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AB - A unified computational fluid dynamics (CFD) method is developed that integrates numerical methods for solving specific problems related to aerodynamic heating phenomena and ablative heatshield. With the use of this unified CFD code, trajectory-based analysis on the aerodynamic heating environment for the MUSES-C superorbital reentry capsule is conducted. Converged solutions can be obtained by loosely coupling the CFD code and the charring materials ablation 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 the existing predictions.

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Unified calculation of hypersonic flowfield for a reentry vehicle

Abstract

ASJC Scopus subject areas

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