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低Re数の二次元翼から発生する後縁ノイズの数値解析
https://jaxa.repo.nii.ac.jp/records/4894
https://jaxa.repo.nii.ac.jp/records/4894c0347837-47c7-4307-b5ec-bfef59aedd94
名前 / ファイル | ライセンス | アクション |
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64575018.pdf (642.2 kB)
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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数の二次元翼から発生する後縁ノイズの数値解析 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | trailing-edge noise, computational aeroacoustics, wake instability | |||||
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 | Numerical simulations of trailing-edge noise generation from 2-D airfoils at low Reynolds numbers | |||||
著者 |
池田, 友明
× 池田, 友明× 高木, 正平× Ikeda, Tomoaki× Takagi, Shohei |
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著者所属 | ||||||
宇宙航空研究開発機構研究開発本部 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構研究開発本部 | ||||||
著者所属(英) | ||||||
en | ||||||
Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
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: 「境界層遷移の解明と制御」研究会講演論文集(第43回・第44回) en : JAXA Special Publication: Proceedings of the 43rd and 44th JAXA Workshops on "Investigation and Control of Boundar-Layer Transition" 巻 JAXA-SP-09-014, 発行日 2010-02-26 |
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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43回(2008年10月2日-10月3日)「境界層遷移の解明と制御」研究会; 第44回(2009年3月26日-3月27日)「境界層遷移の解明と制御」研究会 | |||||
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 | 43rd JAXA Workshops on "Investigation and Control of Boundar-Layer Transition" (October 2-3, 2008) ; 44th JAXA Workshops on "Investigation and Control of Boundar-Layer Transition" (March 26-27, 2009) | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The compressible flows around 2-D airfoils are simulated by using a high-order numerical scheme. In this study, the generation of trailing-edge noise is directly reproduced as the fluctuation in pressure field. Two types of airfoils are investigated: NACA0012 and NACA0006. The obtained results on the vortex-shedding frequencies and the growth rate of velocity fluctuation confirm that the tone noise frequency is determined by the wake instability in both cases. The dipole sound scattered by the acoustically non-compact airfoils shows multiple lobes in the far-field directivity. By imposing non-zero angle of attack, very weak instability waves has little effects on the development of Karman vortex shedding in the present calculation. | |||||
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: AA0064575018 | |||||
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-09-014 |