Research on increasing aircraft aerodynamic efficiency is the main focus of study in aerodynamics. This study compares the performance of the unsplit NACA-0015 airfoil with the NACA-0015 airfoil with a split of 50%c, 60%c, and 80%c. This discussion aims to determine the effect of a split airfoil on unmodified airfoils, preventing flow separation and optimizing CD(drag coefficient) and CL(lift coefficient). This research is based on computational fluid dynamics (CFD) with an AoA range of 00 to 200. This research found that the baseline NACA-0015 performs slightly better than using a split airfoil in CL. However, the split still competes with the baseline, with an average decrease of approximately 6.61% across different split dimensions, delaying the stall. Despite the CL deterioration, the airfoil with a split exhibits lower CD values compared to the unsplit airfoil., with an average 22–23% reduction across all split dimensions. In general, utilizing split airfoils improves the performance of the NACA-0015 airfoil, leading to an average increase in CL/CD of 22.35% across all split dimensions. In summary, the split airfoil outperforms the baseline airfoil.