In aviation, efficient aerodynamic performance is essential, particularly for military and commercial aircraft where reducing drag is critical. This research investigates the impact of split configurations and flow control techniques on a NACA 0012 airfoil model. Experiments and computational fluid dynamics (CFD) simulations investigate a range of split positions, ranging from 0.45 to 0.55c and 0.55c0.007. The airfoil split at 0.55c performs better than the other designs, according to the results. It delays flow separation on the airfoil surface, which greatly reduces drag and improves aerodynamic efficiency especially in comparison with configurations with splits at 0.45, 0.5, and 0.55c. In order to maximize aerodynamic performance, this study emphasizes the significance of split configuration design and the potential benefits of purposefully positioning the divide at 0.5c by aircraft designers to enhance efficiency.