This paper discusses the use of several experimental techniques to investigate the performance and flowfield of a swept wing with leading-edge ice at low Reynolds numbers. Force balance measurements were made over a range of angles of attack and Reynolds numbers. Surface oil visualization and pressure sensitive paint were used to investigate the flow over the surface of the wing, while five-hole probe wake surveys were used to investigate the wake. The flowfield of the iced swept wing was dominated by a leading-edge vortex that formed at low angles of attack due to separation from the tip of the ice shape, while for the clean wing a vortex did not form until higher angles of attack. The effect of Reynolds number on the performance and flowfield was also investigated.