High-aspect-ratio flexible wing undergoing large deflection requires nonlinear structure and aerodynamic model to predict accurate aeroelastic behavior.The paper presents a methodology for high-aspect-ratio flexible wings aeroelastic analysis based on geometrically exact,fully intrinsic beam theory and Extended-ONERA dynamic stall aerodynamic model.By finite element discretization,the governing formulas coupled with nonlinear structure and aerodynamic can be described as first-order algebra differential form.Newton-Raphson method and Backward-Differentiation-Formulas (BDF) method are used for the solutions of static equilibrium and time simulation.Aeroelastic stability of Goland wing and the effects of several parameters on flutter velocity are investigated.The results show that the flutter velocity rises as the incidence or sweep angle increases,and declines with the increasing the ratio of flapwise bending stiffness to torsional stiffness.
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