Journal of the Japan Society for Aeronautical and Space Sciences
巻
63
号
6
ページ
233(1) - 240(8)
発行年
2015-12-05
抄録（英）
The boundary layer transition caused by the cross flow instability over a highly swept wing was controlled by using a DBD plasma actuator. The plasma actuator installed near the leading edge, and induced the flow to suppress the cross flow velocity that causes the transition on the highly swept wing. A low-speed wind tunnel tests were performed to understand the effects of the plasma actuator for a 60 degrees swept wing on Re=487000. The results were shown that when plasma actuator is activated the transition location delayed to downstream than no actuation of the plasma actuator. It means that the plasma actuator contributes to reduce the cross flow velocity component hence the boundary layer transition can be delayed to downstream. With increasing the voltage of the plasma actuator, the displacements of the transition locations are also increased. This trend was also observed at different free-stream velocities.
内容記述
形態: 図版あり
内容記述（英）
Physical characteristics: Original contains illustrations
プラズマアクチュエータによる大きな後退角を持つ翼の境界層制御
