Flow seperation control in leading edge of aerofoil using plasma actuators

The present study focuses on improving the efficiency of an aerodynamic aerofoil by using a plasma actuator to minimize the introduction of flow separation around the leading edge. Methods that use small devices that require extra energy to change the flow are called methods of active flow control l. From this point of view, the use of flow control plasma actuators is a good alternative to encouraging the alteration of the boundary layer profile. For aerodynamic applications, the absence of moving parts and the simple use of power can be interesting features. The actuation was developed with a plasma sheet system (PSD) consisting of two flush bare electrodes mounted on the wing profile's leading edge surface to obtain a discharge in the inter-electrode space contouring the body. Following the aerofoil leading edge curvature and running over 90% of the span, it is worked to achieve a discharge. By applying momentum tangentially to the wall to the boundary layer, the surface dielectric barrier discharge is used to change velocity close to the leading edge. The various angle of attack and flow separation outcomes to be performed should be checked later in the wind tunnel.