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Aims at increasing the wing's lift and weakening the wing's shock wave, flow active control is studied by using the fluid mechanics. A new active control method based on piezoelectric elements is proposed, in which piezoelectric elements are buried on upper surface of winginduces periodic disturbance of boundary layer. The numerical simulation of the aerodynamic characteristics during the deformation process is done using the structural grid and the unsteady flow calculation method. The effect of piezoelectric elements on increasing the lift and weakening the shock of the aircraft wing is analyzed using computational fluid dynamics (CFD). Most previous studies were confined in a two-dimensional air-foil numerical simulation. In this article, its computing method is extended to a three-dimensional wing model to verify the validity of the new control method. Research shows that through appropriate parameter optimization, partial active deformation can improve the aerodynamic characteristics of airfoil. With the low roach number, the lift coefficient can be increased by 15% and the drag coefficient can be descended by 16%. The shock wave will move backward by control in the condition of high roach number and the lift coefficient of symmetrical airfoil can be improved by 17%. The self-adaptive wing can meet aerodynamic needs in variety of conditions. [ABSTRACT FROM AUTHOR]