The performance of an aircraft wing mostly depends on the aerodynamic characteristics i.e. lift force, drag force, pressure distribution, the ratio of lift to drag etc. In this paper, the influence of aerodynamic performance on two dimensional NACA 4412 airfoil is investigated. The computational method consists of steady-state, incompressible, finite volume method, spalart-allmaras turbulence model. The flow has been studied with the help of Navier-Stroke and continuity equations. Numerical simulations were performing at Reynolds number (1x106, 2x106, 3x106, and 4x106) at different angles of attack (0, 3,6, and 9). The results give a satisfactory measure of confidence of fidelity of the simulation. Aerodynamic forces are calculated with different Reynolds number and angle of attack, after analyzing the data it is found that the higher lift coefficient was obtained in Re-4000000 at an angle of attack 90 whereas low drag coefficient was obtained in Re-1000000 at AOA-0.
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