Boundary layer flow control using synthetic jets on the flow over a NACA 0012 airfoil

Numerical simulations of the flow control using a synthetic jet are presented. The flow considered is around a NACA 0012 airfoil at Re = 5000 and the actuator is located at 6% of the chord from the leading edge. This work will be focused on the study of the effect of the frequency of the actuator on the flow parameters in order to find in which range of frequencies the actuation is more efficient.