The rising risks faced by pilots in military missions are changing the global perspective on aviation, where human-piloted aircraft are being progressively substituted by Unmanned Aerial Vehicles (UAVs). UAVs offer a more efficient solution with lower production and operational costs, longer flight duration, and flexible flying capabilities, especially in difficult-to-access conditions or locations. The use of UAVs cannot be separated from studies regarding airfoils. This is because the cross-sectional structure of the UAV wings is in the form of an airfoil. This study aims to analyze the use of passive flow control instruments through a center split airfoil for optimizing the airfoil’s aerodynamic performance. This re-search was modeled using 2D Computational Fluid Dynamic (CFD) simulations on NACA 0015 airfoils with and without center split for Angle of Attack (AoA) varieties of 0°-20° at various Reynolds numbers, which include 2.2 × 105, 2.9 × 105, and 3.6 × 105. The results of this study show that utilization of center split airfoil on NACA 0015 airfoil could prevent early stall, increase lift force at optimum AoA, and reduce drag force.