@inproceedings{oai:jaxa.repo.nii.ac.jp:00004753,
 author = {簗瀬, 祐太 and 木田, 大穂 and 大竹, 智久 and 村松, 旦典 and 本橋, 龍郎 and Yanase, Yuta and Kida, Oho and Otake, Tomohisa and Muramatsu, Akinori and Motohashi, Tatsuo},
 book = {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, JAXA Special Publication: Proceedings of 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010},
 month = {Feb},
 note = {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), 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010 (June 24-25,  2010. Yonago Convention Center BiG SHiP), Yonago, Tottori Japan, 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., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064967046, レポート番号: JAXA-SP-10-012},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {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},
 volume = {JAXA-SP-10-012},
 year = {2011}
}