A visualization study on the boundary layer and near-wake of an NACA 0012 airfoil was con-ducted in order to investigate the influence of boundary layer behavior on the near-wake at low Reynolds numbers. The present study is investigated at static angles of attack ${alpha}=0^{circ},;3^{circ},;6^{circ}$ and $Re=2.3{ imes}10^4,;3.3{ imes}10^4,;4.8{ imes}10^4$ by using a smoke-wire technique. The results of this study show that the laminar boundary layer on the airfoil surface is attached to the surface at ${alpha}=0^{circ}$, and that laminar separation of boundary layer on the airfoil surface occurs at ${alpha}=3^{circ}$. Furthermore, reattachment of the boundary layer occurs in the case of ${alpha}=6^{circ}$. In the current study, the location of the laminar separation point moves upstream as the Reynolds number and the angle of attack increase.