Numerical simulations on NACA0015 airfoil at high angles of attack were performed by using the S-A

standard k-w

and SST k-w turbulence models to reveal the interaction of nanosecond pulse plasma aerodynamic actuation and boundary layer

and the effects of these three turbulence models on aerodynamic simulation accuracy were contrasted.Based on the calculated results

the structure of unsteady separated flow and the frequency spectrum of lift coefficient were analyzed

and the characteristic frequency of the unsteady flow around the airfoil was discovered.Then

wind tunnel experiment was conducted with the coupling between the actuation frequency and the vortex shedding frequency.The results indicate that the unsteady separated flow can be effectively controlled as the actuation frequency is not lower than the vortex shedding frequency

and the lift coefficient of the airfoil is increased by 18.1% and the drag coefficient is reduced by 22.5% when the coming flow velocity is 100 m/s and the angle of attack is 22°.This study may help to reveal the vortex control mechanism of nanosecond pulse plasma aerodynamic actuation and hence to enhance the vortex control ability.