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極超音速流れにおける30 degランプ周りの衝撃波/境界層干渉に関する3次元数値解析
https://jaxa.repo.nii.ac.jp/records/14337
https://jaxa.repo.nii.ac.jp/records/14337f50ead1d-2ed1-49f1-a91e-a5faf0023d33
Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 極超音速流れにおける30 degランプ周りの衝撃波/境界層干渉に関する3次元数値解析 | |||||
言語 | ||||||
言語 | jpn | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
アクセス権 | ||||||
アクセス権 | metadata only access | |||||
アクセス権URI | http://purl.org/coar/access_right/c_14cb | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Three-Dimensional Numerical Study of Shock/Boundary Layer Interaction around Compression Corner with 30 degrees in Hypersonic Flow | |||||
著者 |
武藤, 大貴
× 武藤, 大貴× 坪井, 伸幸× 永井, 大樹× 浅井, 圭介× Muto, Hiroki× Tsuboi, Nobuyuki× Nagai, Hiroki× Asai, Keisuke |
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著者所属 | ||||||
九州工業大学 | ||||||
著者所属 | ||||||
九州工業大学 | ||||||
著者所属 | ||||||
東北大学 | ||||||
著者所属 | ||||||
東北大学 | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu Institute of Technology | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu Institute of Technology | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構宇宙科学研究所 | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA) | |||||
書誌情報 |
宇宙航行の力学シンポジウム: 平成22年度 en : Symposium on Flight Mechanics and Astrodynamics: 2010 発行日 2011-08 |
|||||
会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 宇宙航行の力学シンポジウム 平成22年度 (2010年12月16-17日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県 | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Symposium on Flight Mechanics and Astrodynamics, 2010 (December 16-17, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Three-dimensional Navier-Stokes simulations on shock/shock and shock/boundary layer interactions around compressible corner with 30 deg. in hypersonic flow are presented. The simulation condition is Mach number of 7. The results of the numerical simulations are compared with the experimental results conducted at the hypersonic wind tunnel in the Unlv. of Tokyo. As a result, numerical simulations reveal the detailed structure of shock interaction and boundary layer separation, and capture the vortex structures over the ramp. Large heating appears at the leading edge of the plate and the reattachment point. The numerical results agree with the experimental results qualitatively. It is shown that the vortex structure has an important role on the heat transfer on the surface. | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0065106018 |