The study investigates the use of dielectric barrier discharge (DBD) plasma actuators for boundary layer control on the NACA 23012 airfoil to enhance the aerodynamic performance of short take-off and landing (STOL) aircraft. STOL aircraft have specific operation requirements, including high lift, drag, and angle of attack (AoA) flow stability. Plasma actuators, which energize the boundary layer with electrohydrodynamic forces, are considered a lightweight, non-intrusive, and dynamically responsive flow control solution. The study uses computational simulations in MATLAB to investigate the baseline aerodynamic behavior of an NACA 23012 airfoil and examines how plasma actuators affect critical aerodynamic parameters. Results show that plasma actuators can improve aerodynamic efficiency and be applied for passive flow separation control without incurring weight penalties associated with traditional boundary layer control methods. Future research should focus on 3D modelling and experimental validation, along with energy efficiency optimization for their application in production scale.