Force measurement experiment was conducted to improve the aerodynamic characteristics of 47 degree sweep blunt leading edge delta wing using nanosecond pulse dielectric barrier discharge plasma aerodynamic actuation at the freestream flow velocity of 30m/s. In order to investigate the optimized actuation position

flow control effects at five different actuation positions were studied experimentally.The results show that the actuation position determines flow control effect.Plasma aerodynamic actuation at leading edge of delta wing can significantly improve the aerodynamic characteristics of delta wing and delay stall

while plasma aerodynamic actuations at different spanwise positions on the upper surface have little effect on the flow control.It is also found that flow control effect depends on actuation frequency.When the peak-peak actuation voltage is 13kV and actuation frequency is 200Hz

the flow control effect is best

which increases lift coefficient from 1.31 to 1.44 by 9.6% at attack angle of 30 degree

with lift-drag ratio by 3.3%.