This study reports an investigation into the aerodynamic behaviour of a morphed wing surface to prevent flow separation at high angles of attack. The morphed surface is generated numerically using a novel “decambering” technique predicted by an in-house code, which accounts for flow separation by modifying the local camber line in a steady-state flow. Using another in-house code, this technique is coupled with the Unsteady Vortex Lattice Method to predict the morphing when the flow is unsteady. The morphed surface predicted numerically is implemented experimentally by attaching an external skin-like surface to the leading edge of the wing. The unsteady analysis is carried out using numerical, CFD (Computational Fluid Dynamics) and experiments at a range of angles of attack, including high and post-stall angles of attack. The spectral density of the transient load data is calculated for both baseline and morphed wings. The section coefficient of lift is utilized to study the unsteady variations in stall cell formations across wingspan at different time frames. Unsteady behaviour of morphed surfaces is also used to study separated boundary layer at post-stall.