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We experimentally study the aeroelastic instability boundaries andthree-dimensional vortex dynamics of pitching swept wings, with the sweep angleranging from 0 to 25 degrees. The structural dynamics of the wings aresimulated using a cyber-physical control system. With a constant flow speed, aprescribed high inertia and a small structural damping, we show that the systemundergoes a subcritical Hopf bifurcation to large-amplitude limit-cycleoscillations (LCOs) for all the sweep angles. The onset of LCOs depends largelyon the static characteristics of the wing. The saddle-node point is found tochange non-monotonically with the sweep angle, which we attribute to thenon-monotonic power transfer between the ambient fluid and the elastic mount.An optimal sweep angle is observed to enhance the power extraction performanceand thus promote LCOs and destabilize the aeroelastic system. The frequencyresponse of the system reveals a structural-hydrodynamic oscillation mode forwings with relatively high sweep angles. Force, moment, and three-dimensionalflow structures measured using multi-layer stereoscopic particle imagevelocimetry are analyzed to explain the differences in power extraction fordifferent swept wings. Finally, we employ a physics-based Force and MomentPartitioning Method (FMPM) to quantitatively correlate the three-dimensionalvortex dynamics with the resultant unsteady aerodynamic moment.

Flow-induced oscillations of pitching swept wings: Stability boundary, vortex dynamics and force partitioning