In this paper, the effect of fluid flow on the NASA 4412 2D wing section was studied, using numerical analysis by CFD software to predict aerodynamic performance coefficients on the wing section at different attack angles (0,3, 6,9). The dynamic forces represented by the lifting and drag forces express the airfoils aerodynamic performance coefficient, which are variable values by changing the attack angles. The results show that the higher the angle of attack, the greater the difference in the pressure coefficient on the upper and lower airfoil surfaces. With the results of laboratory experiments and numerical analysis available on the NASA4412 model, it can be inferred by the computational methods of the computational fluid dynamics program to find the characteristics of aerodynamic performance coefficients that can reduce the dependence on wind tunnel for testing. Rat and that will save money and time. Keywords: Computational fluid dynamics, NASA 4412, lift coefficient, drag coefficient