Recent aircraft designs have begun considering higher aspect ratio wings in order to reduce induced drag for improved fuel efficiency. In order to meet airport gate requirements, folding wing-tips have been introduced as a solution to the increased wing-span. Recent numerical studies have suggested such a folding wing-tip solution may be incorporated with spring devices in order to provide an additional gust loads alleviation ability in flight. A series of low-speed wind tunnel tests was conducted using a prototype of such a concept and found that a folding wing-tip with a non-zero relative angle of the folding hinge axis to the stream-wise direction can provide gust loads alleviation. It was also concluded that the weight of the wing-tip may have a strong influence on the hinge stiffness necessary for best performance. The findings from these tests agree with previous simulations in a qualitative manner.