Abstract
The paper presents results obtained for limit-cycle oscillations (LCOs) in high-aspect-ratio wings caused by structural and aerodynamic nonlinearities. The analysis is based on geometrically exact structural analysis and finite-state unsteady aerodynamics with stall. The results indicate that stall limits the amplitude of post-flutter unstable oscillations. At speeds below the linear flutter speed, LCOs can be observed if the stable steady state is disturbed by a finite-amplitude disturbance. A critical disturbance magnitude is required at a given speed and a critical speed is required at a given disturbance magnitude to initiate LCOs. The LCO initiation mechanism can be attributed to the change in structural characteristics of the wing with deformation. It is also observed that the LCO gets increasingly complex with increasing speed. Period doubling is observed at low speeds and as the speed increases the oscillations lose periodicity and become chaotic.
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