A dynamic meshes and CVT interpolated technology are developed to generate interface mapping for CFD/CSD coupling procedure. Computational structural dynamics (CSD) are modeled using finite element equations. Solving aerodynamic force employs Navier-Stokes discretized based cell-centered finite volume framework with dual-time technology. An aeroelastic coupling procedure will perform with loosing coupling CFD/CSD at the same physics time step. Finally, the CFD / CSD coupling computational convergence solution is obtained for a swept wing at M∞=0.8395，α=5.06°, using the developed nonlinear aeroelastic methodology.History of response of the structure and aerodynamic characteristic with time is analyzed. The study shows the developed CFD / CSD coupling procedure is able to compute nonlinear aeroelastic analysis.