@inproceedings{oai:jaxa.repo.nii.ac.jp:00014633,
 author = {森田, 和貴 and 古川, 信夫 and 林, 光一 and 東野, 文男 and Morita, Kazuki and Furukawa, Nobuo and Hayashi, Koichi and Higashino, Fumio},
 book = {宇宙航行の力学シンポジウム　平成16年度, Symposium on Flight Mechanics and Astrodynamics 2004},
 month = {Mar},
 note = {When a space vehicle returns into the earth atmosphere, the gas temperature around the vehicle becomes very high owing to mainly shock compression. To protect the vehicle from such high temperature environment, the problem on the aerodynamic heating should be analyzed precisely. In the present numerical computations, the high temperature air-flow with the real gas effects such as dissociation and ionization is studied to simulate hypersonic flows produced in a conical nozzle of the gun-tunnel placed at the Aoyama Gakuin University. The 2-D Euler code is used together with TVD scheme for shock discontinuity. To simulate the high temperature air-flow produced in a small hypersonic gun-tunnel located at Aoyama Gakuin University, numerical computations are performed by applying the 2-D Euler code with TVD scheme. The real gas effects of high temperature air with dissociation and ionization are taken into account., 資料番号: AA0048089026},
 pages = {102--105},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)},
 title = {2次元ノズル中を伝播する強い衝撃波背後の数値解析},
 year = {2005}
}