Abstract: The characteristics of static aeroelasticity for elastic wing are calculated by two methods.One is solved based on 3-D Euler equations with cell-centered finite-volume algorithm,explicit Runge-Kutta time stepping scheme,on unstructured tetrahedral dynamic meshes.The other is solved based on 3-D N-S equations,with Non-oscillatory,containing No-free-parameters and Dissipative+Lower Upper difference scheme,Baldwin-Lomax turbulence model,on structure C-H shape moving grids.The influence of wing elasticity is determined by structural influence coefficient method.The results show that the elastic deformation generate bending and torsion on the wing.The torsion reduces the effectual attack angle of the elastic sweep wing.In this paper,the lift of elastic wing decreases 27.9% in contrast to the designed rigid wing.