numerical simulation, thermochemical model, two-temperature model, nonequilibrium flow, hypersonic flow, spacecraft reentry, shock wave, dissociation, aerodynamic heating, research and development, energy relaxation, electron temperature
その他のタイトル（英）
Assessment of the two-temperature model for reentry flow simulations
Shizuoka University Faculty of Engineering
Shizuoka University Faculty of Engineering
出版者
宇宙科学研究所
出版者（英）
The Institute of Space and Astronautical Science (ISAS)
雑誌名
宇宙航行の力学シンポジウム 平成14年度
雑誌名(英)
Symposium on Flight Mechanics and Astrodynamics 2002
ページ
9 - 12
発行年
2003-03
抄録（英）
The two-temperature model was assessed for simulating the chemically and thermally nonequilibrium flows around the reentry vehicle. In this analysis, the effect of the parameters for the model on the thickness of the shock layer and the stagnation point heat flux are compared. The flow condition is that the reentry speed is 8.0 km/s at the altitude of 60 km. It was found that the effect of parameters on the thermal nonequilibrium inside the shock layer is significant. But the shock stand-off distance, shock shape, and the heat flux are not affected significantly.
再突入飛行環境のシミュレーションに用いられる2温度モデルの検証
