Robust Feedback Control of Two and Three Dimensional Flow Separation Around a NACA0012 Profile Using Plasma Actuators

摘要

We addressed the practical problem of robustly controlling the unsteady flow separation over an aerofoil, using the plasma actuators' voltage as the control inputs and realistically available real-time velocity measurements as the control outputs. The proposed controller guarantees the exponential regulation of the output measurements to some suitable reference sets, when the steady-state gain of the system is non-zero and of known sign. Accurate numerical simulations of flows past a pitching NACA0012 are performed in order to test the control effectiveness and validate the modelling assumptions. Transient performance have been investigated in different scenarios, for time-varying angles of attack. The proposed controller is able to effectively suppress the separation bubble, as well as the shedding vortices, while achieving robust dynamic performances, with respect to the variation of the uncertain angle of incidence. Three dimensional computations have been reported as well, demonstrating the effectiveness of the proposed control algorithm to completely suppress three dimensional separation bubble.