Numerical Investigation of DBD Plasma actuator Using Phenomenological Model on the Dynamic Stall of Oscillating Airfoils at Low Reynolds Number

Background: The ability to unconventionally flow control and enhancing aerodynamic efficiency has been improved in recent years by Dielectric barrier discharge (DBD) plasma actuators. The purpose of this work is to investigate numerically the effect of (DBD) of the dynamic stall chronology of NACA 0012 oscillating airfoil at low Reynolds numbers at different values of applied Voltage (5-20 KV) and operating Frequencies (5-20 KHz) based on a phenomenological model. Results: The results showed that, during the upstroke, an increase in the applied voltages at constant frequency, increases in the delay of the onset of the dynamic stall during the upstroke cycle and causes an early flow reattachment over the upper surface of the airfoil during the downstroke cycle compared to the baseline airfoil. Conclusions: DBD produced a notable decreasing in the airfoil drag coefficient, increasing in lift coefficient and enhancing int the hysteresis effect among the oscillating cycle. However, when varying the operating frequencies at constant applied voltages, Insignificant improvement is observed.