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JAXA0.44m極超音速衝撃風洞と気流偏向特性試験
https://jaxa.repo.nii.ac.jp/records/5814
https://jaxa.repo.nii.ac.jp/records/5814599b3c43-9bc8-4ec4-9c32-187fc4e796f2
名前 / ファイル | ライセンス | アクション |
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63333003.pdf (2.4 MB)
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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 | JAXA0.44m極超音速衝撃風洞と気流偏向特性試験 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 気流偏向 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 極超音速衝撃風洞 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 極超音速流 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 感圧塗料 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 圧力測定 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 測定装置 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 風洞模型 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | シュリーレン写真法 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 流れの可視化 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | flow deflection | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | hypersonic shock tunnel | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | hypersonic flow | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure sensitive paint | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure measurement | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | measuring instrument | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | wind tunnel model | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Schlieren photography | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | flow visualization | |||||
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 | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Flow-deflection angle calibration of JAXA 0.44 m Hypersonic Shock Tunnel | |||||
著者 |
山崎, 喬
× 山崎, 喬× 中北, 和之× 中川, 宗敬× 渡利, 實× Yamazaki, Takashi× Nakakita, Kazuyuki× Nakagawa, Muneyoshi× Watari, Minoru |
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著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構 | |||||
出版者(英) | ||||||
出版者 | Japan Aerospace Exploration Agency (JAXA) | |||||
書誌情報 |
宇宙航空研究開発機構特別資料: 第77回風洞研究会議論文集 en : JAXA Special Publication: Proceedings of the Wind Tunnel Technology Association 77th Meeting 巻 JAXA-SP-06-026, p. 15-32, 発行日 2007-03-28 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Flow-deflection angle calibration tests were conducted at JAXA 0.44 m Hypersonic Shock Tunnel with a dual-wheel model support system. Surface pressures on upper and lower surfaces of a two-dimensional wedge model were measured to identify the flow deflection angle. The flow around the model was visualized by a schlieren optical system. The tests were conducted at a nominal Mach number of 10.4. The flow-deflection angle was deducted as 0.2 degrees. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1349-113X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA11984031 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0063333003 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: JAXA-SP-06-026 |