Unsteady force measurements of a plunging airfoil at different frequencies and mean angles of attack are used to construct frequency response models. The obtained frequency response models are then used to determine the linearized flow dynamics around each mean angle of attack, where an optimization-based linear system identification is performed to minimize the error between the predicted and measured frequency responses. Converting these models to state space form and writing the entries of the matrices as polynomials in the mean angle of attack, a global, unified unsteady model is developed. The developed reduced order model, represented in a state space form, is suitable for characterizing the nonlinear dynamical characteristics of the flow and the associated dynamics and control of a flying object.
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