As excellent and user-friendly tool for interfacing flow and structural simulations, the Mesh based parallel Code Coupling Interface (MpCCI) technique was introduced to study effect of membrane rigidity on laminar flow separation over NACA 643-218 airfoil model. Two -dimensional (2D) simulations were performed on rigid (aluminum) and membrane (latex) airfoils, and the effects of angle of attack (α) and Reynolds number (Re), on the flow separation over them were analyzed, and the results were confirmed by observing the corresponding lift and drag characteristics. The flow solver was FLUENT 6.3 and structural solver was ABAQUS 6.8-1, both interfaced by MpCCI 3.1. Suitable wind tunnel experiments were conducted to validate the simulation results, and excellent matching was achieved. The flow was seeded with white smokes and the airfoil surface was illuminated by a pulse Nd: YAG laser with its sheet parallel to the flow. The images were captured using Jai (CVM4CL) CCD camera. It has been established that, the laminar flow separation is greatly influenced by the membrane flexibility, and the membrane airfoil has superior flow separation characteristics over rigid one.