This present work investigates an improvement of the aerodynamic performance of a wing at high, including post-stall angles of attack by re-designing its camberline to control the separation of its boundary layer. This is experimentally implemented using an Aluminium secondary skin on the wing surface, which aligns itself to the separated boundary layer at high angles to attack, such that the flow remains attached to it, which otherwise would have separated on the baseline configuration. The shape of the skin, which is now regarded as the active flow surface, is essentially a morphed version of the baseline shape of the wing and is predicted numerically using an in-house code based on a ‘decambering’ technique that 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. In house developed numerical code VLM3D is first validated using this experimental results in predicting the aerodynamic characteristics and is further tested on a rectangular planforms using different wing sections, NACA0012, NACA4415 and NRELS809. The effective morphed flow surface is also used for the baseline wing 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. Numerical morphed surface are generated for 3D flow separation control and design CL accounting unsteady behaviour of the flow at high α. Transitional behavior of morphed surfaces for different wing sections is discussed to provide insight into the unsteady separated boundary layer characteristics. In addition, the present numerical approach, ‘decambering’ is used to check the effectiveness for controlling the laminar separated flow regimes through morphed flow surface. Results indicate that significant improvement in aerodynamic performance can be achieved for flow separation control at high angles of attack including post-stall through this active morphed flow surface.