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東京大学柏キャンパス極超音速風洞の気流特性について
https://jaxa.repo.nii.ac.jp/records/5615
https://jaxa.repo.nii.ac.jp/records/5615c01a20cd-970b-4ac4-a2f9-cb861ef13db4
名前 / ファイル | ライセンス | アクション |
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63742009.pdf (909.6 kB)
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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 | 東京大学柏キャンパス極超音速風洞の気流特性について | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 極超音速風洞 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 性能試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 研究施設 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 圧力分布 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ピトー管 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力特性 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 極超音速ノズル | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | よどみ点圧力 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | よどみ点温度 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | マッハ数 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 高エンタルピー風洞 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | hypersonic wind tunnel | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | performance test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | research facility | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure distribution | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Pitot tube | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic characteristic | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | hypersonic nozzle | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | stagnation pressure | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | stagnation temperature | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Mach number | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | high enthalpy wind tunnel | |||||
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 characteristics of UT-Kashiwa hypersonic wind tunnel | |||||
著者 |
今村, 宰
× 今村, 宰× 綿貫, 忠晴× 鈴木, 宏二郎× 柏風洞ワーキンググループ× Imamura, Osamu× Watanuki, Tadaharu× Suzuki, Kojiro× Kashiwa Wind Tunnel Working Group |
|||||
著者所属 | ||||||
東京大学 大学院新領域創成科学研究科 | ||||||
著者所属 | ||||||
東京大学 大学院工学系研究科 | ||||||
著者所属 | ||||||
東京大学 大学院新領域創成科学研究科 | ||||||
著者所属 | ||||||
東京大学 | ||||||
著者所属(英) | ||||||
en | ||||||
University of Tokyo Graduate School of Frontier Sciences | ||||||
著者所属(英) | ||||||
en | ||||||
University of Tokyo School of Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
University of Tokyo Graduate School of Frontier Sciences | ||||||
著者所属(英) | ||||||
en | ||||||
University of Tokyo | ||||||
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39回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2007論文集 en : JAXA Special Publication: Proceedings of 39th Fluid Dynamics Conference/Aerospace Numerical Simulation Symposium 2007 巻 JAXA-SP-07-016, p. 50-55, 発行日 2008-02-29 |
|||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | In this study, the flow characteristics of UT (University of Tokyo)-Kashiwa hypersonic wind tunnel are obtained by measuring the Pitot pressure distribution. In this wind tunnel, the Mach 7 and 9 hypersonic nozzles are inherited from its predecessor facility in UT-Komaba Campus. From a viewpoint of the operation safety and cost, the maximum stagnation pressure at Kashiwa facility is 950 kPa, which is much lower than at Komaba facility (5 MPa). To evaluate the uniformity of the freestream of this tunnel, the Pitot pressure traverse was conducted for the Mach 7 nozzle by using the rake of 11 Pitot tubes with 20 mm intervals in the radial direction. The measurement has been done at every 30 or 45 degrees in the circumferential direction and also at some streamwise locations. The Mach number calculated from the settling chamber pressure and the test-section static pressure is nearly seven, which is almost the same as the Mach number obtained from the Pitot pressure (about 14 kPa) on the center line. The Pitot traverse shows that the uniform flow core with 120 mm diameter is formed both at the nozzle exit (200 mm in diameter) and at the center of the test section. Such ratio of the core diameter to the nozzle exit diameter seems quite reasonable, comparing to other existing hypersonic wind tunnels. The cross-sectional Mach number distribution shows slight deviation from the axi-symmetric pattern because of the misalignment of the nozzle and the test section to the tunnel center line. Consequently, the highly uniform Mach 7 flow is obtained in this facility, though the nozzle is used under the off-design operation pressure, that is, the off-design Reynolds number. | |||||
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: AA0063742009 | |||||
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-07-016 |