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高速断層シュリーレンによる二次元翼バフェットの可視化
https://jaxa.repo.nii.ac.jp/records/21653
https://jaxa.repo.nii.ac.jp/records/216537edc360f-29a7-4acc-b17a-aa5b87f6ae8d
Item type | 学術雑誌論文 / Journal Article(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2016-02-01 | |||||
タイトル | ||||||
タイトル | 高速断層シュリーレンによる二次元翼バフェットの可視化 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Flow Visualization | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Shock-boundary Layer Interaction | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Supercritical Airfoil | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Two-dimensional Transonic Wind Tunnel | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||
資源タイプ | journal article | |||||
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 | Fast-framing Focusing Schlieren Visualization of Two-dimensional Wing Buffet | |||||
著者 |
山口, 真伍
× 山口, 真伍× 河内, 俊憲× 小池, 俊輔× 中島, 努× 佐藤, 衛× 神田, 宏× 柳瀬, 眞一郎× Yamaguchi, Shingo× Kouchi, Toshinori× Koike, Shunsuke× Nakajima, Tsutomu× Sato, Mamoru× Kanda, Hiroshi× Yanase, Shinichiro |
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出版者 | ||||||
出版者 | Japan Society for Aeronautical and Space Sciences | |||||
出版者(英) | ||||||
出版者 | 日本航空宇宙学会 | |||||
書誌情報 |
日本航空宇宙学会論文集 en : Journal of the Japan Society for Aeronautical and Space Sciences 巻 63, 号 4, p. 166(48)-174(56), 発行日 2015-08-05 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | We visualized two-dimensional wing buffet using fast-framing focusing schlieren method. A supercritical airfoil of NASA SC(2)-0518 was used in this study. Mach number of the freestream was 0.7, and Reynolds number based on the wing code (c) was 5×10(exp 6). Angle of attack without corrections (α) was changed from 4 deg to 6 deg. The present focusing schlieren system had plus or minus 18mm depth of field, which was narrow than spanwise region where the two-dimensionality of the flow field was maintained. 8,345 successive images were captured by high speed CMOS camera with 7,000 frames per second with 20μs exposure time. The present imaging system well captured the shock wave motion on the airfoil. At α = 4 deg, the shock wave was positioned at x/c approximately 0.45. The shock wave was slightly fluctuated with a frequency of 585.5Hz. Above α = 5 deg, the wing buffet occurred. The buffet frequency increased as increasing α. The focusing schlieren movies revealed that the shock wave was bifurcated on the wing surface, as the shock traveling upstream. The boundary layer largely separated from the leading oblique foot of the bifurcated shock wave, whereas, the bifurcated shock wave changed into a normal shock and the flow separation disappeared, as the shock traveling downstream. For both cases, many pressure waves propagated from the downstream of the shock wave to the upstream. These waves merged with the shock wave, and seem to drive the shock oscillation. | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: 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 illustrations | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1344-6460 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA11307372 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: DS1540214007 |