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低Re数の二次元翼から発生する空力音について: 数値手法
https://jaxa.repo.nii.ac.jp/records/4877
https://jaxa.repo.nii.ac.jp/records/48778cfd7d50-24d9-4819-be26-b430f2e932de
名前 / ファイル | ライセンス | アクション |
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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空力音について: 数値手法 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | trailing-edge noise, computational aeroacoustics, acoustic analogy | |||||
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 aerodynamic-noise generation from 2-D airfoils at low Reynolds numbers: Computational aspects | |||||
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 | Aerodynamic noise generated from 2-D airfoils is of interest in conjunction with the development of Karman-vortex shedding in the wake region. In this study, the computational aspects are discussed to reproduce the trailing-edge noise using acoustic analogies, based on the flow field obtained by a compressible flow solver with higher-order numerical schemes. The comparative study indicates that less-expensive acoustic analogies fail in representing the acoustically non-compact sound source with incompressible flow field However, by using a compressible near-field solution, the FW-H equation successfully predicts the far-field sound pressure directivity, for an accurate pressure fluctuation is provided at the airfoil surface. | |||||
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: AA0064575001 | |||||
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 |