The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with a swept angle of 72° at Mach 2 which corresponds to a subsonic leading edge. The transition location was determined using a constant temperature hot-wire anemometer. A comparison of the influence of small angles of attack on the transition position with a model with a supersonic leading edge is shown. The transition to a wing model with a subsonic leading edge occurs earlier than on a wing model with a supersonic leading edge. The angle of attack has a significant effect on the position of the transition point from the laminar to turbulent flow. The data presented in the article are among the first results for a swept wing with a subsonic leading edge.