This paper presents the development of an aeroelastic analysis formulation for the dynamic response of a flexible wing. The geometric nonlinear structure is represented by a reduced order model (ROM) that accounts for the large motion effects on the inertia and stiffness terms. It is based on a system identification of a built-up FEM model and does not rely on geometric nonlinear beam-based FEM as most of the state-of-the-art nonlinear aeroelastic frameworks do. The complexity of the wing structural layout is captured in the built-up FEM as in traditional industry applications. To preserve a small number of states to represent the structural dynamics of the system, modal approach is used in a nonlinear sense. Moreover, this approach leads to easy link with CFD. For this study, the structural ROM framework is integrated within the aeroelastic solution of the CFD code CFL3D. Using this integrated solution, the aeroelastic response of a high-aspect-ratio wing is investigated.
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