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磁力支持天秤装置による運動するデルタ翼機模型の非定常空力計測
https://jaxa.repo.nii.ac.jp/records/46347
https://jaxa.repo.nii.ac.jp/records/463473e1d5023-f86b-4d99-a19b-ef3084d5e6a3
名前 / ファイル | ライセンス | アクション |
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AA1930011006.pdf (2.1 MB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2020-02-04 | |||||
タイトル | ||||||
タイトル | 磁力支持天秤装置による運動するデルタ翼機模型の非定常空力計測 | |||||
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 | Unsteady Aerodynamic Measurements of Moving Delta Wing Model Using Magnetic Suspension and Balance System | |||||
著者 |
甲斐, 大貴
× 甲斐, 大貴× 杉浦, 裕樹× 手塚, 亜聖× Kai, Daiki× Sugiura, Hiroki× Tezuka, Asei |
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著者所属 | ||||||
早稲田大学 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
早稲田大学 | ||||||
著者所属(英) | ||||||
en | ||||||
Waseda University | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Waseda University | ||||||
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: 第51回流体力学講演会/第37回航空宇宙数値シミュレーション技術シンポジウム論文集 en : JAXA Special Publication: Proceedings of the 51st Fluid Dynamics Conference / the 37th Aerospace Numerical Simulation Symposium 巻 JAXA-SP-19-007, p. 107-112, 発行日 2020-02-04 |
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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51回流体力学講演会/第37回航空宇宙数値シミュレーション技術シンポジウム (2019年7月1日-3日. 早稲田大学早稲田キャンパス国際会議場), 新宿区, 東京 | |||||
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 | 51st Fluid Dynamics Conference / the 37th Aerospace Numerical Simulation Symposium (July 1-3, 2019. International Conference Center, Waseda University), Shinjuku-ku, Tokyo, Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Forced oscillation wind tunnel tests were conducted on a delta wing model with a 60 deg swept leading edge using JAXA's 60 cm high angle of attack (AOA) magnetic suspension and balance system (MSBS) wind tunnel. The pitch axis dynamic derivatives of the model were measured, and the effects of the center AOA of oscillation, oscillation amplitude, and oscillation frequency were surveyed. The loci of the aerodynamic longitudinal components varied complexly according to oscillation center AOA, amplitude, and frequency; however, in cases of oscillation center AOA of 0 degree and frequency of 1 Hz, the loci of pitching moment tended to vary in similar form with increase of the oscillation amplitude. The degree of scatter of the dynamic derivatives tended to be larger at higher angles of attack. | |||||
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 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA1930011006 | |||||
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-19-007 |