Wingtip devices are such important components of the current generation of aircrafts; they significantly decrease drag and consequently increase the aircraft’s performance. This work is devoted to the examination of the effectiveness of the wing-tip shapes within subsonic flight. Through the CFD simulations in ANSYS fluent the variation of cant angles from 15° to 75° on aerodynamic parameters was analyzed for the tapered blended winglet utilizing NACA 2412 airfoil for defining the geometry of the wing. Outcomes are outlined pointing to the fact that the configuration with the cant angle of 45° yields the best performance, reductions in the induced drag and improvements of the L/D ratio. The influence of Angle of Attack (AoA) in defining the aerodynamic efficiency of a wing with and without winglet is also analysed. The results highlight that wingtip designs accessible through advanced technology contribute to sustainable aviation by providing higher efficiency and minimizing the effects on the physical environment.