Control of dynamic flowfield around a pitching NACA633−618 airfoil by a DBD plasma actuator

High-fidelity computations of the flow control around a pitching NACA633−618 airfoil by a plasma actuator are conducted. The effectiveness of the plasma actuator and the effects of its installation position are investigated. The plasma actuator is installed at x/c=0%, 10%, and 60% from the leading edge of the airfoil. The installation position of 60% is chosen based on the investigation of the uncontrolled flowfield; the case with this position successfully enhanced the aerodynamic performances of the airfoil. The results show the importance of a priori investigation of the separation and the reattachment points for an uncontrolled flowfield. In addition, the results illustrate that a properly installed and actuated plasma actuator is capable of controlling the dynamic flowfields and improving the aerodynamic performances of an airfoil.