Abstract
A feedforward controller based on the nonlinear Goman-Khrabrov state space model is designed to compensate for the adverse lift and moment effects resulting from an airfoil pitching in a post-stalled state. The lift hysteresis is shown to be strongly dependent on the reduced frequency, so controllers based on simple synchronization with angle of attack are not likely to work at off-design conditions. The Goman-Khrabrov state space model is shown to accurately predict the lift over a wide range of frequencies and under quasi-random pitching conditions. The model is implemented in a feedforward controller that adjusts the amplitude of a short-duty cycle piezo-electric actuator located near the leading edge of the airfoil. Both periodic and quasi-random pitching motions within the stalled region are used to demonstrate the effectiveness of the control approach. The relatively long time delay believed to be associated with the recovery of the separated flow state limits the controllable bandwidth to kâ<â0.1.
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An, X., Grimaud, L., Williams, D.R. (2015). Feedforward Control of Lift Hysteresis during Periodic and Random Pitching Maneuvers. In: King, R. (eds) Active Flow and Combustion Control 2014. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 127. Springer, Cham. https://doi.org/10.1007/978-3-319-11967-0_4
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DOI: https://doi.org/10.1007/978-3-319-11967-0_4
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