At present time, the use of fixed-wing Micro Aerial Vehicles (MAV) is challenged by limited operation windows due to weight restrictions on the batteries and the decreased performance due to early onset of stall at high angles of attack. Aiming to overcome this problem, a hybrid active-passive stall control system was previously proposed for a wing with leading-edge tubercles. However, the active control system requires additional power, which is problematic with current batteries due to their excessive weight. Hence, this work focused on the feasibility of mounting a fringe-type piezoelectric device at the trailing-edge of the wing for energy harvesting. The device oscillates with the shedding of the vortices from the tubercled wing to power the active stall control system. A physical model was explored to find the device whose resonant frequency matched best the vortex shedding frequency of the wing. Another model was used to predict the voltage output of the device operating at this frequency. Based on the results of the former, selected devices were put to the test in a wind tunnel. The power density ratio harvested by the most promising device ranged 〖10〗^(-5) W/kg for a light weight of about 50 mg. The voltages in closed-circuit were observed to be in the order of 60 mV, with the open-circuit voltages reaching 300 mV. Additionally, the wing with the piezoelectric fringe has shown to be able of producing a slightly higher lift-to-drag ratio than the clean wing at high incidence.

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