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デルタ形状ボルテックスジェネレーターによる後縁フラップ上の剥離流れ制御について
https://jaxa.repo.nii.ac.jp/records/22623
https://jaxa.repo.nii.ac.jp/records/22623c59fb948-9f3f-4ef8-bce5-3542a0a9f3bd
Item type | 学術雑誌論文 / Journal Article(1) | |||||
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公開日 | 2015-08-17 | |||||
タイトル | ||||||
タイトル | デルタ形状ボルテックスジェネレーターによる後縁フラップ上の剥離流れ制御について | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Aerodynamics | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | High Lift Device | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Vortex Generator | |||||
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 | Control of Flow Separation on Trailing Edge Flap Using a Delta-Shaped Vortex Generators | |||||
著者 |
郭, 東潤
× 郭, 東潤× 雷, 忠× 野口, 正芳× Kwak, Dongyoun× Lei, Zhong× Noguchi, Masayoshi |
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著者所属 | ||||||
宇宙航空研究開発機構航空本部(JAXA) | ||||||
著者所属 | ||||||
諏訪東京理科大学 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構航空本部(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Aeronautical Technology, Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Tokyo University of Science, Suwa | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Aeronautical Technology, Japan Aerospace Exploration Agency (JAXA) | ||||||
出版者 | ||||||
出版者 | 日本航空宇宙学会 | |||||
出版者(英) | ||||||
出版者 | The Japan Society for Aeronautical and Space Sciences | |||||
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 3, p. 83(7)-88(12), 発行日 2015-06-05 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Low-speed wind tunnel tests were performed to investigate aerodynamic effects induced by delta-shaped vortex generators installed on the upper surface of a trailing-edge flap. The vortex generator was applied to control the flow field around the trailing-edge flap where the flow was separated from the hinge line of the trailing-edge flap. The test results showed that the vortex generators increase the lift coefficient and the lift-to-drag ratio when the trailing-edge flap deflects to 30 degrees. The leading-edge separation vortices formed from the delta-shaped vortex generators suppressed the flow separation on the trailing-edge flap. The height of the vortex generator geometrically changes depending on the trailing-edge flap deflection angles. Therefore, when the trailing-edge flap is not deflected such as cruise flight condition where the flow field is dominated by the attached flow, the vortex generator does not impose a penalty on the aerodynamic performance. | |||||
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: PA1520038000 |