Through applying phenomenological model of nanosecond pulse dielectric barrier discharge（NS-DBD） actuation to the leading edge of delta wing

the flow control simulation was conducted over a 47° blunt-edged delta wing. The variations of lift coefficients and drag coefficients at different attack angles

as well as the evolutions of flow structure and induced vortex

were analyzed. The results show that

if ignited at the reduced frequency of F+=1.44

the actuation can obviously improve the lift coefficients before and after stall

and the drag coefficients also increased

and kept consistent with the experimental results. Chordwise vortex induced by every actuation could change the structure of the leading-edge separated shear layer and cause it to curl inwards. There were obvious negative pressure peak values on the wings upper surface for the time-averaged flow field with actuation. Also

the flow reattachment was promoted and the region of backflow was reduced under NS-DBD actuation.