When a reentry vehicle enters the planetary atmosphere, a strong shock wave is generated and the strong aerodynamic heating appears. Gas temperature in front of the vehicle exceeds 10,000K and chemical reactions (ionizations and dissociations) occur behind the shock wave. Because the reentry vehicle is damaged by the aerodynamic heating, accurate evaluation of the aerodynamic heating in high-enthalpy flow is necessary for design and development of the vehicle. In this paper, three-dimensional numerical analysis was conducted to consider an angle of attack and unstructured grids were used to make it easy to generate computational grid around the vehicle with complicated shape. We reproduced the actual flow field around ARD (Atmospheric Reentry Demonstrator) which was launched by the European Space Agency (ESA) in 1998 and revealed the aerodynamic heating and flow properties. In the solver used here, thermochemical nonequilibrium was assumed and temperature was separated into translational, rotational, vibrational and electron temperature. For chemical model, 11 chemical species and 49 reactions are considered. The computational result showed good agreement with measured pressure at the stagnation by the flight experiment.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
大気圏再突入時におけるESA ARD回りの高エンタルピー流に関する非構造格子解析モデルの検証
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