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低Re数翼周り流れの境界層不安定と音響変動との相関について
https://jaxa.repo.nii.ac.jp/records/4713
https://jaxa.repo.nii.ac.jp/records/4713c7a34b30-2889-4fb6-b116-4518fb690b0f
名前 / ファイル | ライセンス | アクション |
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64967006.pdf (1.5 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 | 低Re数翼周り流れの境界層不安定と音響変動との相関について | |||||
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 | On the correlation between boundary-layer instability and acoustic disturbances in low Re number flow around an airfoil | |||||
著者 |
跡部, 隆
× 跡部, 隆× 池田, 友明× Atobe, Takashi× Ikeda, Tomoaki |
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著者所属 | ||||||
宇宙航空研究開発機構研究開発本部流体グループ | ||||||
著者所属 | ||||||
宇宙航空研究開発機構研究開発本部流体グループ | ||||||
著者所属(英) | ||||||
en | ||||||
Fluid Dynamics Group, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Fluid Dynamics Group, Aerospace Research and Development Directorate, 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42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 論文集 en : JAXA Special Publication: Proceedings of 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010 巻 JAXA-SP-10-012, 発行日 2011-02-28 |
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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42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 (2010年6月24日-25日. 米子コンベンションセンター BiG SHiP) | |||||
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 | 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010 (June 24-25, 2010. Yonago Convention Center BiG SHiP), Yonago, Tottori Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The unsteady aerodynamics of a two-dimensional NACA0006 airfoil are investigated at a low Reynolds number, directly resolving acoustic perturbations in subsonic flows. At a relatively low angle of attack, periodic vortex sheddings are reproduced, simultaneously generating a dipole sound from the trailing edge. By slightly altering inflow Mach number, the shedding frequency often changes drastically, presumably via the onset or offset of an acoustic feedback loop, which correlates an aerodynamic sound emission from the trailing edge, and an instability mechanism in the suction-side boundary layer of the foil. In this study, the phase difference between two different waves - an emitted sound wave and an induced instability wave, is statistically sampled and examined to clarify the on/off determination mechanism of the acoustic feedback loop. | |||||
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 | |||||
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: AA0064967006 | |||||
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-10-012 |