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遷音速フラッタ風洞における二次元フラッタ試験について
https://jaxa.repo.nii.ac.jp/records/5161
https://jaxa.repo.nii.ac.jp/records/5161b5fc5f98-b80a-440c-96d8-d5f6e767456d
名前 / ファイル | ライセンス | アクション |
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64474004.pdf (1.2 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 | 遷音速フラッタ風洞における二次元フラッタ試験について | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Aeroelasticity, Transonic flow | |||||
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 | Two dimensional flutter experiment in transonic flutter wind tunnel | |||||
著者 |
齊藤, 健一
× 齊藤, 健一× 菊池, 孝男× 玉山, 雅人× 有薗, 仁× Saito, Kenichi× Kikuchi, Takao× Tamayama, Masato× Arizono, Hitoshi |
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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 (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
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80回風洞研究会議論文集 en : JAXA Special Publication: Proceedings of the Wind Technology Association 80th meeting 巻 JAXA-SP-09-004, 発行日 2009-12-28 |
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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 | 第80回風洞研究会議(2008年5月15日-5月16日) | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Elastic support system was developed to perform two dimensional aeroelastic test in transonic flutter wind tunnel of JAXA. Two dimensional wing which has supercritical wing profile was tested to obtain static pressure distribution and Limit Cycle Oscillation (LCO) property. Stability boundary observed in the test showed transonic dip which has the bottom at Mach 0.79. Amplitude of LCO is about 0.2 to 0.5 degree in pitching motion. Flow conditions were corrected so as to eliminate the difference of steady pressure distribution between experiment and numerical analysis. | |||||
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 | |||||
内容記述(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Wind Tunnel Technology Association Meeting | |||||
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: AA0064474004 | |||||
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-09-004 |