In this report, a low-speed airfoil over the NACA 0012 airfoil at 2° and 14° attack angles with the given inlet velocity of 0.25 m/s, was modeled and computational fluid dynamic (CFD) analysis were performed using FLUENT in Ansys. The Reynolds number based on the chord is roughly Re=2.88×〖10〗^6. The flow was modeled as incompressible and inviscid. All setup and procedures were done by following the steps provided Cornel University website. Though, mesh independence was achieved for 2° attack angle, for 14° attack angle; which is more than the stall angle, mesh independence was not achieved. Lift and drag coefficient increases as the number of mesh element or the attack angle increases.