Abstract: It is important for big plane to increase lift and decrease drag.In this paper,the main content are focused on the numerical simulation of passiveness flow control technique and initiative flow control technique,including micro-vortex generators,contour bump,and zero mass jet flow.The mechanism of flow control and effects of parameters using tiny flow control part are analysed.Numerical simulation methods are used to investigate on the viscous pressure drag reduction effect with micro-vortex generators located on the supercritical wing.The results indicate that appropriate tallness of micro-vortex generators will avail to control flow separation,the best efficiency will relate setting location.Numerical simulation methods are also used to investigate on the wave drag reduction effect with contour bump located on the supercritical airfoil.If contour bump is effectively adopted on the supercritical airfoil at the wave feet area,wave drag will be reduced.And under moderate-to-high lift coefficient conditions,contour bump increases the lift-to-drag ratio of the supercritical airfoil remarkably.The numerical simulation results of zero mass jet flow located on the airfoil indicate that both the average lift coefficient and the average drag coefficient are added with the increase of the jet flow velocity,and the effects of the jet flow frequency on lift are non-linear.