Abstract
Summary This paper discusses the effect of fibre orientations, composite skin lay-up, bending-torsion material coupling, and the root flexibility or stiffness of a composite rectangular wing box model for different fibre orientations on the dynamic and aeroelastic analysis (flutter and divergence speeds) for the Circumferentially Uniform Stiffness (CUS) and Circumferentially Asymmetric Stiffness (CAS) configurations.