In order to improve the stall characteristics of the non-slender delta wing at high angles of attack and explore the influence of the leading-edge shape on the flow control effect, wind tunnel experiments on the flow control of the non-slender delta wings are carried out based on alternating current dielectric barrier discharge (AC-DBD) plasma actuation. In view of three delta wing models with radius of curvature at leading-edge being different, the influence of actuation parameters on the flow control effect is studied. The results show that the lift coefficient of delta wing with sharp leading-edge shape is slightly higher than that of other two kinds of delta wings with blunt leading-edge shapes at small angle of attack. The maximum lift coefficient of delta wing with circular leading edge is the highest. The leading-edge actuation directed towards the wing's upper surface is the best control effect on the lift coefficient before the stall angle of attack, whereas the leading\|edge actuation directed towards the wing’s lower surface is the best control effect after the stall angle of attack. The round-shape leading edge delta wing is the best control effect. The lift under condition of the same actuation voltage (12 kV) for the sharp, round and elliptical leading edge delta wings can be increased by 3.6%, 5.9% and 4.2% respectively at the post-stall stage. The optimal dimensionless pulsed actuation frequency is f+=1to2, and the optimal duty cycle is 5%. The higher the voltage amplitude, the better the control effect. The analysis shows that main mechanism of AC-DBD actuation control of non-slender delta wings is its unsteady disturbance to the shear layer rather than the effect of body force. The distribution of leading\|edge kinetic energy affects the formation of induced stream-wise vortices, and the difference of leading-edge shapes makes a different effect of flow control for no-slender delta wings eventually achieve.