In recent years, Plasma actuators have strengthened the ability to control flows in creative manners leading to improvements in lift, drag reduction, and aerodynamic efficiency. These advancements could result in safe, more effective, and quiet aircraft.  A numerical investigation is performed to determine the influence of Dielectric barrier Discharge (DBD) plasma on the flow properties of NACA 0012 airfoil at low Reynolds numbers, considering various angles of attack. The modified baseline airfoil was examined at three applied voltages 6.85 kV, 8.38 kV, and 11.45 kV at constant frequency. The results demonstrated that, when compared to the baseline airfoil, the DBD plasma actuator delays the trailing edge flow separation. Moreover, at 11.45 kV, the flow maintains attached to the airfoil at an angle of 20º and entirely eliminating the flow separation. Furthermore, the DBD airfoil significantly rising the lift coefficients while reducing the drag coefficients.