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アイテム
極超音速TSTO空力干渉流れ場における2物体間隔の空力加熱率への影響
http://hdl.handle.net/2237/13879
http://hdl.handle.net/2237/138794efbf328-bae5-4f9c-9ab3-b68f05e0f4e1
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
jjsass_v53_n622.pdf (1.7 MB)
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| アイテムタイプ | 学術雑誌論文 / Journal Article(1) | |||||
|---|---|---|---|---|---|---|
| 公開日 | 2010-07-27 | |||||
| タイトル | ||||||
| タイトル | 極超音速TSTO空力干渉流れ場における2物体間隔の空力加熱率への影響 | |||||
| 言語 | ja | |||||
| その他のタイトル | ||||||
| その他のタイトル | Effect of the Clearance between Two Bodies on TSTO Aerodynamic Heatin | |||||
| 著者 |
西野, 敦洋
× 西野, 敦洋× NISHINO, Atsuhiro× 石川, 尊史× ISHIKAWA, Takahumi× 北村, 圭一× KITAMURA, Keiichi× 中村, 佳朗× NAKAMURA, Yoshiaki |
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| アクセス権 | ||||||
| アクセス権 | open access | |||||
| アクセス権URI | http://purl.org/coar/access_right/c_abf2 | |||||
| キーワード | ||||||
| 主題Scheme | Other | |||||
| 主題 | Two Stage To Orbit (TSTO) | |||||
| キーワード | ||||||
| 主題Scheme | Other | |||||
| 主題 | Hypersonic Flow | |||||
| キーワード | ||||||
| 主題Scheme | Other | |||||
| 主題 | Shock/Shock Interaction | |||||
| キーワード | ||||||
| 主題Scheme | Other | |||||
| 主題 | Shock/Boundary-Layer Interaction | |||||
| キーワード | ||||||
| 主題Scheme | Other | |||||
| 主題 | Temperature Sensitive Paint (TSP) | |||||
| キーワード | ||||||
| 主題Scheme | Other | |||||
| 主題 | Heat Flux | |||||
| 抄録 | ||||||
| 内容記述タイプ | Abstract | |||||
| 内容記述 | TSTO (Two Stage To Orbit) is a candidate for advanced space transportation system, which is required to fly over a wide region from subsonic to hypersonic speed with an orbiter connected with a booster. The hypersonic flow field with aerodynamic interaction around a TSTO model, which consists of a delta wing as a booster and a hemisphere-cylinder as an orbiter, has been investigated. The temperature distribution is measured by the Temperature Sensitive Paint (TSP) method, and the heat flux with thermo-couples. As a result, the flow field has been significantly affected by the clearance between the two bodies. In the case of a small clearance, heat flux on the head of the hemisphere-cylinder becomes about 3.1 times as large as the stagnation heat flux for the hemisphere-cylinder alone. On the other hand, at a large clearance, heat flux on the delta wing becomes about 1.1 times as large as the stagnation heat flux. In addition, a new thermal protection system (TPS) to reduce the aerodynamic heating due to shock/shock interaction and shock/boundary-layer interaction is also investigated in this paper. A triangular prism installed on the delta wing can change the aerodynamic heating, depending on its location. It was found that a small device installed upstream is effective, where the heat flux has been reduced by about 48%. | |||||
| 言語 | en | |||||
| 出版者 | ||||||
| 出版者 | 日本航空宇宙学会 | |||||
| 言語 | ja | |||||
| 言語 | ||||||
| 言語 | jpn | |||||
| 資源タイプ | ||||||
| 資源タイプresource | http://purl.org/coar/resource_type/c_6501 | |||||
| タイプ | journal article | |||||
| 出版タイプ | ||||||
| 出版タイプ | VoR | |||||
| 出版タイプResource | http://purl.org/coar/version/c_970fb48d4fbd8a85 | |||||
| ISSN | ||||||
| 収録物識別子タイプ | PISSN | |||||
| 収録物識別子 | 1344-6460 | |||||
| 書誌情報 |
ja : 日本航空宇宙学会論文集 巻 53, 号 622, p. 503-509, 発行日 2005-11-05 |
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| フォーマット | ||||||
| 値 | application/pdf | |||||
| 著者版フラグ | ||||||
| 値 | publisher | |||||
| URI | ||||||
| 識別子 | http://hdl.handle.net/2237/13879 | |||||
| 識別子タイプ | HDL | |||||
