Numerical study on unsteady aerodynamic characteristics of an airfoil with a synthetic jet set in trailing edge

In order to obtain a new device for aircraft dynamic control, a low frequency, high-power synthetic jet set in trailing edge is presented. The unsteady flow of NACA 0012 airfoil with the synthetic jet set in trailing edge is simulated by numerical method. The effects of orifice form, jet momentum coefficient and reduced frequency on lift coefficient and moment coefficient are studied. It is demonstrated that the low frequency, high-power synthetic jet set in trailing edge can modify the lift and moment effectively. The amplitudes of lift and moment increase with the jet momentum coefficient, while decrease with reduced frequency, and the phase delay of the airfoil aerodynamic characteristic coefficient will be increase with the reduced frequency.