NACA aerofoil shapes have been successfully used over the years as wing and tail sections for general aviation and military aircraft, as well as propellers and helicopter rotors. The aircraft performance is highly affected by induced drag caused by wingtip vortices to improve fuel efficiency. In this research work, the analysis of NACA 66-206 aerofoil propellers was investigated for high-speed aircraft propulsion.CFD analysis is performed on the NACA aerofoil to verify the aerodynamic characteristics and enhancing the lift of the aircraft by changing the orientation of angle of attack 0 0 , 10 0 and 20 0 and to determine the drag and lift coefficients by applying inlet velocities. An auxiliary part, winglets are added on propeller blade tip in order to improve the performance of propeller. By adding this auxiliary equipment the weight of propeller are significantly increased. To decrease the weight without compromising the performance of the propeller the fiber reinforced composite materials are used. The effects of stacking sequence layers of composite materials, which were fabricated from Kevlar, carbon, glass fibres, and epoxy resin have been used to increase the strength to weight ratio. To validate the strength of the propeller, Structural and buckling analysis is performed.