Research for the improvement in aerodynamics performance of Micro Air Vehicle at low attack angle using plasma actuator

点击翻译按钮获取中文摘要

The lift coefficient of thick airfoil becomes essentially zero at low Reynolds number and low attack angle, for the laminar separated flow does not reattach at the trailing edge. According to the increase in the attack angle, the laminar separated region becomes unstable and the flow becomes oscillatory, which lead to the flow reattachment and the steep increase in the lift coefficient. This research demonstrated that, by installing a plasma actuator near the trailing edge of the airfoil and artificially inducing steady flow or oscillatory flow, we can increase the lift coefficient.