In this study, the aerodynamic performance of the NACA 6412 wing, which is widely used in aerodynamic systems with its high-performance ratio feature, is optimized using the Taguchi Method to simultaneously evaluate the effects of multiple parameters and to reduce the number of Computational Fluid Dynamics (CFD) experiments to an optimum level. Within the framework of the Design of Experiments (DOE) methodology, the analyses were carried out in the Reynolds number range Re = 100,000-200,000 to determine the optimum design conditions by considering five main factors: maximum camber (bmax), maximum camber position (x), angle of attack (alpha), maximum thickness (tmax), and free-flow velocity (V). In this direction, CFD simulations based on the Taguchi L16 orthogonal array were performed and the data obtained were statistically evaluated using Analysis of Variance (ANOVA). The lift-to-drag ratio (CL/CD) obtained from the optimum experimental parameter combination (NACA5310) determined by the Taguchi method is compared with the basic NACA 6412 airfoil and 16 other configurations included in the analysis. The results show that the optimized airfoil provides an improvement in performance of approximately 17% compared to the NACA 6412 airfoil.