@inproceedings{oai:jaxa.repo.nii.ac.jp:00006448,
 author = {大津, 広敬 and 安部, 隆士 and Otsu, Hirotaka and Abe, Takashi},
 book = {宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2004論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2004},
 month = {Mar},
 note = {An applicability of the electrodynamic heat shield system to a super-orbital reentry vehicle was investigated. In the case of the super-orbital reentry flight, due to the strong ionization reactions inside the shock layer, the electrodynamic heat shield system is expected to work well. In order to evaluate the ambiguity of the thermochemical model on the efficiency of this heat shield system, a CFD analysis including thermochemical non-equilibrium effect was performed. The flight condition used for the present study is that the velocity is 11.6 km/sec at the altitude of 64 km. From the CFD result, it was found that the ambiguity of the thermochemical model on the electrodynamic heat shield system is negligible. Additionally, it was found that the stagnation point heat flux could be reduced by about 1.0 MW/sq m when the magnetic field strength of 0.5 T is applied., 資料番号: AA0048469008, レポート番号: JAXA-SP-04-012},
 pages = {51--56},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {再突入飛行体のCFD解析における熱化学モデルの影響について:電磁力を利用した空力加熱低減法への影響},
 volume = {JAXA-SP-04-012},
 year = {2005}
}