Divergence characteristics of a subsonic composite wing with control surface have been analyzed using finite element method and vortex lattice method. Eigenvalue problem has been set up to obtain the divergence characteristics of a composite wing with control surface deflection. The shear deformable finite element method is used for the structural analysis and the linear vortex lattice method is applied for the aerodynamic analysis. A surface spline interpolation scheme is employed to interconnect the structural nodal and aerodynamic control points. Wings considered in this analysis, are forward swept and unswept composite(T300/5208 Graphite/Epoxy) wings. Divergence performance is highly dependant on the fiber orientation. The effect of a control surface on the divergence is significant for the specific fiber orientation.
