عنوان مقاله [English]
The purpose of this research is to use the artificial jet actuator to control the boundary layer with the approach of improving the aerodynamic performance of NASA GAW-2 supercritical airfoil in the post-stall region. In this research, unsteady Navier-Stokes equations were solved in turbulent and incompressible flow conditions using Fluent software. In this research, the excitation frequency factor has been studied as a parameter influencing the flow control by the artificial jet actuator. The results are presented for three dimensionless frequencies 1, 3 and 5. Under the effect of dimensionless frequency 5, the highest increase in the coefficient of attack was obtained for the angle of attack of 18 degrees, which has increased by 10% compared to the maximum for the uncontrolled state. The biggest decrease in the drag coefficient is related to the dimensionless frequency of 5 and the angle of attack of 20 degrees, in which the drag coefficient has decreased by 37% compared to the uncontrolled state. In the best control mode, the separation point is delayed by 25.8% of the chord length.