Investigations of aeroelastic response for a system with continuous structural nonlinearities

Measurements and predictions of aeroelastic response are examined for a wing section mounted to permit continuous nonlinear structural response. Nonlinear behavior is introduced using a unique model support system designed to permit prescribed nonlinear stiffness characteristics. The wing section is limited to pitch and plunge response. Tailored experiments establish nonlinear responses such as limit cycle oscillations, and these results are predicted with an analytical model.

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