The effect of fiber orientation on the deformation pattern and aerodynamic coefficients of the cantilevered composite wing is investigated. The wing structure is assumed as a plate-like wing. The finite element method that accounts for the transverse shear deformation has been used for the structural analysis. The vortex lattice method has been applied to the various-shaped thin wings for the aerodynamic analysis. The aerodynamic forces are interpolated to the structural nodal forces by the surface spline method. The deformed shape of a wing and redistributed aerodynamic forces are obtained from an iteration procedure. Various-shaped thin wings are analyzed and the flexibility effect of the laminated composite wing is investigated. ; 항공우주공학전공