In the present study, the numerical study is carried out for boundary layer flow over 3D aerofoil section and the aerodynamic performance of NACA aerofoil are analyzed by studying the lift and drag coefficient of the aerofoil.The results obtained in the case of boundary layer flow over the 3D aerofoil section are compared with the experimental data as available in the literature. The experimental data for NACA 64-009 from wind tunnel is validated with simulations results computed in FLUENT. The aerofoil is cambered and measured to be around 1mt. The simulations for boundary layer flow for NACA 64-009 is performed at various angles of attacks. In addition, the lift coefficient, drag coefficient, pressure contour and velocity contour are computed.