To improve the delta-wing aerodynamic characteristic at high angle of attack

the schlieren test under static atmosphere

PIV measurement at different angles of attack

and force measurement under different parameters by microsecond pulse dielectric barrier discharge（SDBD） were conducted. It is shown that SDBD can result in instant heating which induces compressional wave locally and can effectively control the flow separation of low-speed delta wing at high angle of attack. With increase in the angle of attack

the effect of flow control will be weakened until disappearing. There is an optimal frequency which is the most efficient for flow control. When the free-stream velocity is 30 m/s

the optimal frequency is 80 Hz and the non-dimensional frequency is 1

which can increase the maximum lift coefficient of delta wing by 4.3% and delay the stall angle of attack with 2°. At the same angle of attack

the effect of flow control is better at free-stream velocity of 45 m/s than that at 30 m/s.