The aeroelastical problem of large aspect ratio wing is analysed in the paper. In the static aeroelastic analysis, Navier Stokes equations based on cell-centered finite volume discretization is used to obtain aerodynamic performance. To generate a grid for CFD simulation, a moving grid method is developed. Finite element equations is used to compute structural dynamics, a coupling computational method of CFD and CSD is developed and a numerical simulation study of static aeroelastic for three-dimensional aircraft wing is carried out. Then modal analysis for the high aspect ratio wing model, based on modal analysis results, the static analysis model was modified iteratively to get a rational dynamic model. The flutter analysis for the wing were done in the evaluation of unsteady aerodynamics by lifting surface theory.
