In order to explore the mechanism of dielectric barrier discharge at high angle of attack on the highlift wing, the simulation of the aerodynamic characteristics of the highlift wing with the coupling of the body force model and the Eddy Viscosity Transport Equation turbulence model is carried out. The simulation model is validated by comparing the experimental data with the simulation model at the flow velocity of 45 m/s. The model is used to analyze the streamlines of the chordwise and spanwise sections of the wing. The results show that the DBD at the leading edge of the wing can obviously improve the aerodynamic characteristics of highlift wing at high angle of attack, improve the vortex structure of the upper airfoil and control the separated flow. The maximum lift coefficient of the wing increases by 111％ and the stall angle of attack is delayed 2°. And also, with the angle of attack increasing, the effect of flow control is gradually weakened until disappearing.