Abstract: The subsonic turbulence flow over 30P30N three-element airfoil is simulated numerically at high angle of attack. In order to control the flow separation in the leeward in the cases of high angle of attack, a traveling wave model and an active oscillating model are added to the upper surface of the airfoil. Then the unsteady flows over the morphing airfoil are simulated with an unsteady flow solver based on dynamic hybrid grids, which was developed in previous work. The numerical results show that, in some cases, the flow separation in the leeward will be depressed and even completely eliminated so that the lift coefficient can be increased and the drag coefficient can be cut down to improve the aerodynamic performance of the airfoil at high angle of attack.