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極超音速流中のエアロスパイク付き鈍頭物体の表面熱流束について
https://jaxa.repo.nii.ac.jp/records/14448
https://jaxa.repo.nii.ac.jp/records/1444826e2d5d8-a1ab-405b-8294-03bf6e81d9e4
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 極超音速流中のエアロスパイク付き鈍頭物体の表面熱流束について | |||||
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 | Surface Heat Flux on a Blunt-Nosed Body with an Aerospike in Hypersonic Flow | |||||
著者 |
坪井, 伸幸
× 坪井, 伸幸× 永井, 大樹× 河勝, 元× 浅井, 圭介× 中北, 和之× Tsuboi, Nobuyuki× Nagai, Hiroki× Ha, Seunwon× Asai, Keisuke× Nakakita, Kazuyuki |
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著者所属 | ||||||
宇宙航空研究開発機構宇宙科学研究本部 | ||||||
著者所属 | ||||||
東北大学 | ||||||
著者所属 | ||||||
東北大学 | ||||||
著者所属 | ||||||
東北大学 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構研究開発本部 | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS) | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)(ARD) | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構宇宙科学研究本部 | |||||
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 en : Symposium on Flight Mechanics and Astrodynamics 巻 平成20年度, 発行日 2009-12 |
|||||
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20年度)(2008年12月4~5日、宇宙航空研究開発機構宇宙科学研究本部) | |||||
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 2008 (December 4-5, 2008. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)), Sagamihara, Kanagawa Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | A blunt body in hypersonic flow is subjected to severe aerodynamic heating and drag. This is one of the most critical problems of designing the hypersonic vehicles such as Reusable Launch Vehicles(RLV). It is well khown that spiked nose(aerospike) concept is effective for aerodynamic drag reduction on asymmetric blunt bodies in hypersonic flow.In this study, we investigated the heat flux distribution on a blunt-nosed body with an aerospike in hypersonic flow. The spike length and the angle of attack were changed to verify the heat reduction effect. The experiment was conducted at Mach 10 in the JAXA 0.44-m Hypersonic Wind Tunnel and the temperature of body was measured by using. Temperature-Sensitive Paint, which is a global temperature measurement technique based on photochemical reaction. In addition, the heat flux distribution calculated increase rate of temperature. The flow field around a blunt-nosed body is visualized by schlieren images and compared with TSP images and CFD results to discuss the heat flux disbibution. It was found from the result that the heat flux distribution is changed widely with the angle of attack. In this study, moreover, the heat-flux and the flow field relation were clarified by shock/shock interaction analysis of the flow field for different angle-of-attack. | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0064729025 |