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DBDプラズマアクチュエータを用いた低レイノルズ数領域におけるNACA0012 翼の空力特性の改善
https://jaxa.repo.nii.ac.jp/records/4753
https://jaxa.repo.nii.ac.jp/records/47532e021599-90ca-41ea-8c5a-9e9923de901d
名前 / ファイル | ライセンス | アクション |
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64967046.pdf (1.6 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 | DBDプラズマアクチュエータを用いた低レイノルズ数領域におけるNACA0012 翼の空力特性の改善 | |||||
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 | Enhancement of Aerodynamic Characteristics of NACA 0012 Airfoil with a DBD Plasma Actuator at Low Reynolds Numbers | |||||
著者 |
簗瀬, 祐太
× 簗瀬, 祐太× 木田, 大穂× 大竹, 智久× 村松, 旦典× 本橋, 龍郎× Yanase, Yuta× Kida, Oho× Otake, Tomohisa× Muramatsu, Akinori× Motohashi, Tatsuo |
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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 | ||||||
日本大学理工学部 | ||||||
著者所属 | ||||||
日本大学理工学部 | ||||||
著者所属(英) | ||||||
en | ||||||
Nihon University | ||||||
著者所属(英) | ||||||
en | ||||||
Nihon University | ||||||
著者所属(英) | ||||||
en | ||||||
Nihon University | ||||||
著者所属(英) | ||||||
en | ||||||
College of Science and Technology, Nihon University | ||||||
著者所属(英) | ||||||
en | ||||||
College of Science and Technology, Nihon University | ||||||
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 effects of a DBD plasma actuator applied to a NACA0012 airfoil were examined at a Reynolds number of 10,000 using three approaches, namely, aerodynamic force measurements using a wind tunnel balance, velocity profiles of the wake obtained using a hot-wire anemometer, and smoke-wire visualization around the airfoil. As a result, the magnitude of lift approximately doubled and the drag was reduced by about 30 percents. The lift curve changed from nonlinear to linear at the lower angles of attack below 6 degrees with actuator operation. These phenomena are occurred by suppression of flow separation near the leading edge. This separation was suppressed by a downwash induced by the actuator operation. Though there might be some limitation in the performance of the plasma actuator against the angle of attack, the plasma actuator enhanced the aerodynamic performance of the airfoil under our experimental conditions. | |||||
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: AA0064967046 | |||||
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 |