University of Tokyo Graduate School
University of Tokyo Graduate School
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science
出版者
宇宙航空研究開発機構
出版者（英）
Japan Aerospace Exploration Agency (JAXA)
雑誌名
宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2006論文集
雑誌名(英)
JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2006
巻
JAXA-SP-06-010
ページ
89 - 94
発行年
2006-12-01
抄録（英）
This paper investigates effective layout of a dielectric barrier discharge plasma actuator for a flow separation control on the NACA0012 wing using computational simulations. The flow condition of low speed and low Reynolds number, M(sub infinity) = 0.1 and Re = 1.0 x 10(exp 5) is considered. Three cases of locations of the actuators are simulated. The actuator is placed at the 5 percent, 10 percent and 20 percent chord from the leading edge for each case. When the low velocity is induced by the actuator, the location has little effect on the capability to suppress the flow separation. However, if the higher velocity is induced, the actuator placed near the separation point can provide the better capability. Further increasing the angles of attack, another separation occurs from the trailing edge. Then the actuator placed near the leading edge can not suppress such separation. This is the control limitation of the single actuator. The result motivates use of the multiple plasma actuators for effective separation control.
プラズマアクチュエータを用いた翼周り流れの制御
63154017.pdf
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