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Abstract: Wind tunnel and flight experiments were performed on a general aviation 6.1:1 scale model, where pulse-modulated dielectric barrier discharge (DBD) plasma actuators were used to control wing stall. Plasma actuation on the unpowered model produced modest increases in maximum lift coefficient, while post-stall lift coefficients never dropped below the baseline (non-actuated) maximum. Flow visualization revealed that actuation fully attached the outboard flow while also preventing inboard leading-edge stall. Powered wind tunnel tests showed that the propeller wake promotes, or exacerbates, separation at post-stall angles of attack, but these effects are partially overcome by actuation, which delivers a 6% reduction in stall speed. Flight experiments, performed while gliding, showed that actuation dramatically reduces uncontrolled pitch, roll and yaw, and loss of altitude. By preventing massive separation, actuation facilitates safe and stable flight at angles of attack at, and greater than, the baseline static stall angle. The DBD plasma stall control system can easily be retrofitted to a full-scale general aviation aircraft, or integrated into the wing design.