Folding wing-tips have begun to feature on recent aircraft designs, as a solution for compliance with existing airport gate width, whilst the higher aspect ratio will lead to lower induced drag and better overall fuel efficiency. Recent studies have suggested that by allowing folding of the wing-tip during flight, additional gust load alleviation can be achieved. This paper describes the follow-on work from a previous experimental study, in which the folding wing-tip concept is now applied to a new wind tunnel model of a high aspect ratio wing with a much-reduced bending stiffness. Using a low-speed wind tunnel with a vertical gust generator, the experiment examined the load alleviation performance through a range of one-minus-cosine gust inputs and found up to 11% reduction in peak wing-root bending moment. In addition, a movable secondary aerodynamic surface was fitted to the folding wing-tip which demonstrated that such a device was able to control the orientation of the folding wing-tip effectively in steady aerodynamic conditions, as well as achieving further reduction in peak wing-root bending moment during gust encounters through active control.