JAXA Repository / AIREX 未来へ続く、宙(そら)への英知

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title2次元ノズル中を伝播する強い衝撃波背後の数値解析
Other TitleNumerical simulation on strong shock waves propagating in a two-dimensional nozzle
Author(jpn)森田 和貴; 古川 信夫; 林 光一; 東野 文男
Author(eng)Morita, Kazuki; Furukawa, Nobuo; Hayashi, Koichi; Higashino, Fumio
Author Affiliation(jpn)青山学院大学 大学院; 青山学院大学 理工学部; 青山学院大学 理工学部; 東京農工大学 工学部
Author Affiliation(eng)Aoyama Gakuin University Graduate School; Aoyama Gakuin University College of Science and Engineering; Aoyama Gakuin University College of Science and Engineering; Tokyo University of Agriculture and Technology Faculty of Engineering
Issue Date2005-03
PublisherInstitute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)
宇宙航空研究開発機構宇宙科学研究本部
Publication title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
Start page102
End page105
Publication date2005-03
Languagejpn
AbstractWhen 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.
Keywordstwo dimensional flow; shock wave propagation; shock compression; nozzle flow; spacecraft reentry; aerodynamic heating; hypersonic wind tunnel; numerical analysis; numerical simulation; real gas effect; 2次元流; 衝撃波伝播; 衝撃圧縮; ノズル流; 宇宙機再突入; 空力加熱; 極超音速風洞; 数値解析; 数値シミュレーション; 実在気体効果
Document TypeConference Paper
JAXA Categoryシンポジウム・研究会
SHI-NOAA0048089026
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/30128


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