The aerodynamic performance of low Reynolds number (≤ 5.0 × 10⁵) airfoils, for instance, the airfoils of micro air vehicles and the small-to-medium scale wind turbines, is strongly influenced by the laminar boundary-layer separation. The boundary layer on the suction surface of airfoil may separate due to adverse pressure gradient, and form a large wake behind the airfoil, resulting in deteriorated aerodynamic performance. Therefore, it is crucially important to deploy flow control techniques for achieving lift enhancement and stall angle-of-attack postponement. With promising advantages, such as ultra-low mass, no moving mechanical part and rapid response time, the dielectric barrier discharge plasma actuator has been demonstrated successfully as an effective electro-hydrodynamics device for flow separation control over airfoils.