The flutter analysis for plate like composite wings has been performed using the finite element method based on the shear deformable theory. Doublet-point method is adopted for evaluating three-dimensional, unsteady, aerodynamic forces on lifting surfaces in supersonic flow. A surface spline interpolation procedure is employed to interconnect the structural nodal and aerodynamic control point. The effects of composite filament angle and wing sweep angle on the vibration and flutter characteristics of a composite cantilever plate in supersonic flow are examined numerically. From the numerical examination performed, it is concluded that substantial improvement upon flutter/divergence caracteristics can be achived by using composite materials.
