Aeroelastic Behavior of Composite Wings in Compressible Flow

In this paper، the aeroelastic behavior of composite wings has been studied. Anisotropic thick/thin beam with closed cross section is utilized as structural model. Circumferentially asymmetric stiffness layup scheme is used to obtain the preferred coupling between bending and torsion modes. Aerodynamic strip theory in conjunction with the indicial aerodynamic is used to obtain the aerodynamic loads in compressible flight speeds. To validate the aeroelastic model and results، comparisons between the obtained results and those available in the literature were performed and an excellent agreement was reported.