@inproceedings{oai:jaxa.repo.nii.ac.jp:00003864,
 author = {丸山, 央貴 and 大竹, 智久 and 村松, 旦典 and Maruyama, Hiroki and Ohtake, Tomohisa and Muramatsu, Akinori},
 book = {宇宙航空研究開発機構特別資料: 第46回流体力学講演会/第32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, JAXA Special Publication: Proceedings of the 46th Fluid Dynamics Conference / 32nd Aerospace Numerical Simulation Symposium},
 month = {Mar},
 note = {第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム (2014年7月3日-4日. 弘前文化センター), 弘前市, 青森県, 46th Fluid Dynamics Conference / 32nd Aerospace Numerical Simulation Symposium (July 3-4, 2014. Hirosaki Bunka Center), Hirosaki, Aomori, Japan, In low Reynolds numbers region's flow, a laminar separation region and separation bubble are observed on an airfoil surface, these separation flow contribute to deterioration aerodynamics of the airfoil. We intended to improve the aerodynamics of a NACA0012 airfoil using a pulsed DBD plasma actuator as a flow control device for suppressing the separated flow. We visualized the flow field around the NACA0012 airfoil and measured aerodynamic forces of the airfoil to examine an effect of induced flow by the plasma actuator at 30,000 of Reynolds number. The actuator was only driven in a pulsed modulation wave mode which both of the duty ratio DR and non-dimensional modulation frequency F(+). As the results, we confirmed that a maximum lift coefficient and a stall angle were changed by flow field existing vortices on the airfoil surface which depend on F(+) changing., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1530023029, レポート番号: JAXA-SP-14-010},
 pages = {163--167},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {Re＝30,000におけるDBDプラズマアクチュエータを用いた翼面上の境界層剥離の抑制: 変調周波数と渦の挙動の関係},
 volume = {JAXA-SP-14-010},
 year = {2015}
}