Abstract
A high-precision doubly curved quadrilateral thin shell finite element is used. The composite material property is included using classical lamination theory, and the supersonic aerodynamic effect is included using linearized piston theory. The normal modes approach is adopted. Results are presented for composite plates and curved panels, and composite cylindrical and conical shells. Parametric studies concerning the effects of boundary conditions, fiber orientation, degree of orthotropy, and flow angle on the flutter characteristics are presented
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