A model with main wing and flap which is based on NACA0025 airfoil is used in this paper to study the pulsed blowing effect on flow separation over flap. The effects of average blowing momentum coefficient and Stroul number on flow separation over the flap have been discussed at first. Furthermore, thecontrol effect of this pulsed blowing technique under different deflection angle of flap isdiscussed to make sure whether the control effect of pulsed blowing can meet the needs under different deflection angle of flap. All the research works have been finished by numerical simulation method under conditions of 0deg angle of attack of the main wing.

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