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極超音速におけるリブレットの摩擦抵抗低減効果に関する予備検討
https://jaxa.repo.nii.ac.jp/records/47327
https://jaxa.repo.nii.ac.jp/records/47327617792fa-286c-4fc5-9d99-25763994b547
名前 / ファイル | ライセンス | アクション |
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AA2030013006.pdf (2.2 MB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2021-02-08 | |||||
タイトル | ||||||
タイトル | 極超音速におけるリブレットの摩擦抵抗低減効果に関する予備検討 | |||||
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 | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Preliminary Study on Reduction in Skin-Friction Drag by Riblets in Hypersonic Flow Regime | |||||
著者 |
古谷, 元和
× 古谷, 元和× 渡邉, 保真× 鈴木, 宏二郎× FURUYA, Motokazu× WATANABE, Yasumasa× SUZUKI, Kojiro |
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著者所属 | ||||||
東京大学 | ||||||
著者所属 | ||||||
東京大学 | ||||||
著者所属 | ||||||
東京大学 | ||||||
著者所属(英) | ||||||
en | ||||||
The University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
The University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
The University of Tokyo | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構(JAXA) | |||||
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: 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2020オンライン論文集 en : JAXA Special Publication: Proceedings of Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online 巻 JAXA-SP-20-008, p. 43-46, 発行日 2021-02-08 |
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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 | 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2020オンライン (2020年9月28日-30日. 日本航空宇宙学会 : 宇宙航空研究開発機構(JAXA)オンライン会議) | |||||
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 | Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online (September 28-30, 2020. The Japan Society for Aeronautical and Space Sciences : Japan Aerospace Exploration Agency (JAXA), Online meeting) | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The riblet is the surface configuration that has tiny grooves aligned regularly in a flow direction. In a low-speed flow regime, it is known that the riblet can reduce the skin friction drag by up to 10% by manipulating the vortices over the surface. Thanks to the recent rapid advancement in micro-machining technology, putting the riblet over the surface of an aircraft will become practical in the near future. Reduction in the skin-friction drag by the riblet is also expected in the hypersonic flow regime, because the flow speed is essentially low near the bottom of the boundary layer over the surface even in such high-speed flight. However, little amount of studies on the hypersonic riblet have been made so far. In the present study, the flow over the flat plate model with the riblet was experimentally investigated at the Mach 7 hypersonic wind tunnel in the Kashiwa campus, the University of Tokyo. The preliminary results were presented in this paper. | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: カラー図版あり | |||||
内容記述(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Physical characteristics: Original contains color illustrations | |||||
ISSNONLINE | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 2433-2232 | |||||
著者版フラグ | ||||||
出版タイプ | VoR | |||||
出版タイプResource | http://purl.org/coar/version/c_970fb48d4fbd8a85 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA2030013006 | |||||
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-20-008 |