Variable camber wings (VCWs) adapt to various flight conditions by adjusting the curvature of wings. Most research focuses on replacing the wing’s main structure with the morphing alternatives. The present study gives a new scheme by integrating the skin morphing into the rigid flap. Two kinds of regional skin morphing are considered. Firstly, the skin near the flap hinge at Region I (SM1) is morphed for a smoother downstream configuration. Secondly, the upper skin before the hinge at Region Ⅱ (SM2) is morphed to increase the smooth of the streamline. Both the rigid flap and skin morphing are integrated into a base configuration of NACA0012 airfoil. The aerodynamic benefits from the skin morphing at Regions I and Ⅱ are analyzed by Computational Fluid Dynamics (CFD) simulation. The effects of morphing position and morphing amplitude are also analyzed. The numerical results show that the foil with skin morphing I has higher maximum lift coefficient (CLmax) than the rigid flap foil with 5.6% increasement, and lower drag coefficient (CD) with 13.5% decrease at AoA of 14°. While the foil with skin morphing II has higher stall AoA than the rigid flap foil with 13.3% increasement. The stall delay mechanism is discussed by comparing the velocity streamline and pressure contours. The combined skin morphing schemes are presented from the parametric study with moderate SM1 (d = 5°,10°, xm = 0.6) and leading-edge SM2 (xtmax = 0.25, 0.40, h = 5 mm) to increase lift (CL) at low AoAs (α < 14°). At high AoAs (α > 14°), a moderate SM1 (d = 5°, xm = 0.6) combined with trailing-edge SM2 (xtmax = 0.55, h = 5 mm) is recommended to suppress the flow separation and delay the stall with 2° of AOA, which increases the laminar area by 10 times from the un-morphing foil. This study provides a potential application of skin morphing into VCWs with high aerodynamic performance.