A static aeroelastic analysis that can calculate aerodynamic loads for deformed shape of the generic wing configuration has been performed. This study enables us to predict the interaction between the flexible wing structure and aerodynamic forces. This analysis consists of two methods. One is the finite element method(FEM) for plate structural analysis, and the other is the linear vortex lattice method (VLM) for aerodynamic analysis based on linearized potential theory. The final deformed shape of wing due to applied forces is determined by iterative manner using FEM and VLM. FEM analysis and VLM analysis are related by a surface spline interpolation procedure. Three types of wings (rectangular straight wing, swept forward wing and swept back wing) have been investigated to see the wing flexibility effect for both isotropic aluminum and T300/5208 Gr/Ep composite material. Aerodynamic load change due to wing flexibility is examined. This paper also presents the effect of fiber orientation on the deformation pattern, aerodynamic coefficients and the location of center of pressure for three types of composite wings. The forward swept wing has the most significant flexibility effect. The fiber orientation of composite wing gives significant effect on aerodynamic coefficients and deformation pattern. The optimum fiber orientation to prevent divergence of wing is also discussed.
