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RE=30,000におけるNACA0012翼まわりの流れ場の数値計算
https://jaxa.repo.nii.ac.jp/records/3636
https://jaxa.repo.nii.ac.jp/records/36363c3d7830-2665-4cb8-8ce3-a867a1f4822a
名前 / ファイル | ライセンス | アクション |
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AA1630005011.pdf (2.4 MB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2016-04-21 | |||||
タイトル | ||||||
タイトル | RE=30,000におけるNACA0012翼まわりの流れ場の数値計算 | |||||
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 | Numerical analysis of flow field around a NACA0012 airfoil at Re=30,000 | |||||
著者 |
橋爪, 俊樹
× 橋爪, 俊樹× 大竹, 智久× 村松, 旦典× Hashizume, Toshiki× Ohtake, Tomohisa× Muramatsu, Akinori |
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著者所属 | ||||||
日本大学 | ||||||
著者所属 | ||||||
日本大学 | ||||||
著者所属 | ||||||
日本大学 | ||||||
著者所属(英) | ||||||
en | ||||||
Nihon University | ||||||
著者所属(英) | ||||||
en | ||||||
Nihon University | ||||||
著者所属(英) | ||||||
en | ||||||
Nihon 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47回流体力学講演会/第33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 47th Fluid Dynamics Conference / the 33rd Aerospace Numerical Simulation Symposium 巻 JAXA-SP-15-013, p. 79-84, 発行日 2016-03-08 |
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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47回流体力学講演会/第33回航空宇宙数値シミュレーション技術シンポジウム (2015年7月2日-3日. 東京大学生産技術研究所), 目黒区, 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 | 47th Fluid Dynamics Conference /the 33rd Aerospace Numerical Simulation Symposium (July 2-3, 2015. Institute of Industrial Science , the University of Tokyo), Meguro-ku, Tokyo, Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | We calculated flow around a NACA0012 airfoil at angle of attack 7 degrees in Re=30,000 by using Open FORM to investigate a separation bubble on the upper surface side. In Re=30,000, the laminar separation was formed and the flow on the leading edge was affected by a separation bubble. The pressure distribution from the leading edge to 30% chord was constant. The flow on 50% chord reattached to a wing surface. In lower-Reynolds-number (Re=20,000), the pressure distribution on the upper surface was approximately constant from 20% chord to 80% chord. The flow on the trailing edge changed three-dimensionally. The flow field in higher-Reynolds-number (Re=40,000) was similar to the flow field in Re=30,000. We confirmed a difference in the flow on the upper surface by changing of the Reynolds number. | |||||
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: AA1630005011 | |||||
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-15-013 |