This study reports an investigation into the improvement of the aerodynamic performance of a rectangular wing at high (including post-stall) angles of attack by re-design of its camber to control flow separation and operate at design coefficient of lift (Cl). This is achieved by implementing a secondary morphed skin on the wing surface at high angles of attack such that the flow remains attached to the skin, which otherwise would have separated on the baseline configuration. The active morphed flow surface is generated numerically using a novel ‘decambering’ technique, which accounts for the local deviation of camber by accounting for the difference in coefficients of lift and pitching moment predicted by viscous and potential flows. First, this technique is tested on two different baseline wing sections, NACA0012, and NACA4415 on a rectangular plan form and then with morphed shape configurations. Furthermore, an effective morphed flow surface is also developed to operate at a design local 2D Cl, which is obtained by incrementing the baseline Cl by a user-defined percentage at design pre and post-stall angles of attack. This effective morphed surface is implemented experimentally by attaching an external Aluminium skin to the leading edge of the wing. Aerodynamic characteristics of the morphed configurations using the numerical approach, CFD, and wind tunnel experiments are presented.