A winglet is attached at the edge of the wingsto enhance the performance of the aircraft and reduces the induced drag in the form of wingtip vortices. The winglet is a upstraight or different cant angle at the tips of each wing, with a leading edge featuring tubercle and triangle shape configuration. This article presents 3-D analysis of winglets on a tapered wing using NACA0012 airfoil. The numerical study was conducted to investigate the effect of applying different shapes on the leading edge of blended winglet configurations on the performance of the wing of an aircraft at different velocities are 20, 30 and 50 m/s and at different angles of attack of 0°, 5°, 15°, 20° and 25°. The span of the tapered wing configuration was 250 mm and two different leading edge shape configurations were analysed with variations in sizes and shapes of the leading edge. The primary goal of the analysis is to evaluate the aerodynamic properties of various winglet configurations and to investigate the performance of the two winglet forms modelled at the given cant angle (90° and 120°). The Ansys Fluent solver used the Finite Volume Approach to perform the computational simulations. The Spalart Allmaras solver was used to simulate low subsonic flow and varied angles of attack. The various parameters were investigated in the simulation such as CL, CD, and CP. In this research work the flow separation region is discussed using contour plots..