A fluid/structure coupled method is developed to predict the flutter boundary of NLR7301 airfoil. In the aerodynamics domain, the time-dependant aerodynamic force on the surface of the airfoil is computed by solving the unsteady Reynolds averaged Navier-Stokes equation. Coupled with a structure dynamics equation of the airfoil, the surface displacement of the airfoil is computed. With a dynamic mesh-deformation technique, the interior nodes of the CFD grid is moved accordingly in order to reflect the motion of the airfoil surface, thus the time history of the airfoil self-excited vibration is simulated.