Numerical Simulation of several Structures of PlasmaActuators and Their Performance Assessment over NACA 0012 and NACA 0015 Airfoils

The Plasma Actuators (Dielectric Barrier Discharges) are strong tools for active flow and boundary layercontrol that cause to postpone the location of separation point on control surfaces which recently have been a focus point for aerospace scientists and engineers. In first stages، standard structure of DBD (include one-particle encapsulated electrode) was used in researches، but recently a new structure which include a three particles encapsulated electrode is employed. Encapsulated three-particle electrodes cause to recover the body force of plasma actuator and increase the induced velocity، significantly. In this paper by Electro-Static Lumped-element numerical method is applied and validated. Then، the three-particle and one-particle plasma actuators are used for NACA0012 and NACA0015 airfoils. It is numerically shownthat the separation point displaces back and the pressure distribution is changed favorablyusing DBD. It is also found that the effectiveness of three-particle structure is considerably higher than the standard structure. This research was performed at Rec=1. 0 x106 and the plasma actuator simulated for high voltage AC power supply up to 14kV_ (p-p) with 10 kHz frequency in steady state condition.