The wind tunnel experiments of separation flow control by a nanosecond-pulse-driven dielectric-barrier-discharge plasma actuator (ns-DBDPA) for three airfoil shapes of NASA-Common-Research-Model (NASA-CRM), Gottingen387, and NACA0015 airfoils were conducted and the results were compared. Aerodynamic forces, surface pressures, and particle image velocimetry images were obtained in the experiments. The results of the aerodynamic force and surface pressure measurements showed that the characteristics of the flow separation control by ns-DBDPA are clearly different depending on the airfoil shape, and particularly the type of stall. NACA0015 exhibited leading-edge stall under the conditions investigated, and ns-DBDPA achieved flow control by producing vortices. NASA-CRM exhibited thin-airfoil stall, and ns-DBDPA increased the maximum lift of the lift curve even after the stall. On the other hand, Gottingen387, which exhibited trailing-edge stall, achieved almost no flow control at any actuator position, actuation frequency, or voltage amplitude. The flow control mechanisms for different types of airfoils are discussed based on the particle image velocimetry measurement results.

NASA-Common-Research-Model (NASA-CRM)、Gottingen387 和 NACA0015 三种翼型的纳秒脉冲驱动介质阻挡放电等离子体致动器 (ns-DBDPA) 的分离流控制风洞实验进行了并比较了结果。在实验中获得了空气动力、表面压力和粒子图像测速图像。空气动力和表面压力测量的结果表明，ns-DBDPA 的流动分离控制特性明显不同，具体取决于翼型形状，尤其是失速类型。NACA0015 在所研究的条件下表现出前沿失速，而 ns-DBDPA 通过产生涡流实现了流量控制。NASA-CRM 展出薄翼型失速，即使在失速之后，ns-DBDPA 也增加了升力曲线的最大升力。另一方面，Gottingen387 表现出后缘失速，在任何致动器位置、致动频率或电压幅度下几乎没有实现流量控制。基于粒子图像测速测量结果讨论了不同类型翼型的流动控制机制。