Computational Fluid Dynamics (CFD) has emerged as an indispensable tool for simulating and analyzing the aerodynamic characteristics of aircraft components. This paper uses the open-source software OpenFOAM to determine the aerodynamic performance of a NACA 64008a airfoil. The simulations employ the Reynolds-Averaged Navier-Stokes (RANS) equations coupled with the Spalart-Allmaras turbulence model to capture the turbulent effects. The computational methodology, mesh generation, boundary conditions, and initial conditions are validated with experimental data for the NACA 0012 airfoil. The simulations are then applied to predict the aerodynamic performance of the NACA 64008a airfoil. The results depict the lift, drag, and pressure distribution at various angles of attack. Detailed analysis of the pressure field around the airfoil provides insights into the formation and development of leading-edge and trailing-edge vortices, which play a crucial role in determining the overall performance. The pressure coefficient (Cp) distribution along the chord length (x/c) of the NACA 64008a airfoil at different angles of attack (AOA) is presented. The relationship between the lift coefficient (Cl) and the angle of attack (α) for the NACA 64008a airfoil is also investigated. Furthermore, the variation of the drag coefficient (Cd) with the angle of attack (α) for the NACA 64008a airfoil is examined. These insights can be used to guide future design optimization efforts