Abstarct: Over the years since the construction of the world's first aircraft, one of the ongoing challenges faced by aerodynamic engineers has been the reduction of induced drag. One of the most effective solutions for reducing this drag is the installation of a device known as a winglet at the wingtip. Reducing induced drag leads to an increase in aircraft range as well as a reduction in fuel consumption and environmental pollutants. The focus of this research is on achieving higher values of aerodynamic efficiency. All simulations were conducted using ANSYS Fluent software. In this study, the simulation and validation of the NACA 0012 airfoil and the ONERA wing were first carried out. The validation results for the ONERA wing showed an error of 1.96% for the lift coefficient and 0.47% for the drag coefficient. The results indicated that selecting appropriate geometric parameters can significantly improve the aerodynamic performance of the wing. Among the configurations related to cant angle and length, the wing equipped with Winglet No. 2, which has 1.5 times the length of Winglet No. 1, showed the best performance with a 23.9% increase in aerodynamic efficiency and a 35.66% increase in lift at a cant angle of 30 degrees and an angle of attack of 2 degrees compared to the wing without a winglet. On the other hand, among the configurations related to cant angle and tip twist angle, the wing equipped with a winglet without a tip twist angle showed the best performance with a 19.22% increase in aerodynamic efficiency and a 26.12% increase in lift at a cant angle of 30 degrees and an angle of attack of 2 degrees compared to the wing without a winglet. Finally, baxsed on the results of the parametric analysis of winglet performance, a guideline was provided for optimizing the winglet geometry to achieve the best aerodynamic efficiency under various flight conditions.