The invention provides a natural laminar-flow supercritical wing section applied to a sweepback wing of an intermediate range civil airplane. The natural laminar-flow supercritical wing section has the following pressure distribution form: a bump appears in a front edge area of an upper surface, i.e., an area with a chordwise range of 0 to 5 percent C, a pressure coefficient height of the bump is 0.05, a bump area accounts for 0.3 percent of a whole pressure distribution area, which is used for inhibiting the unstable disturbance development of a three-dimensional cross-flow CF wave; and a favorable pressure gradient is kept in an area from the back of the bump to a shock wave position, which is used for inhibiting the unstable disturbance development from a two-dimensional flow to a TS wave. The natural laminar-flow supercritical wing section has the advantages that the development of the two-dimensional TS wave disturbance and the three-dimensional cross-flow CF wave disturbance can be simultaneously inhibited, the transition of boundary laminar flow occurring in the front edge area when the wing section is arranged on the sweepback wing can be avoided, so that a relatively large-scale natural laminar flow can still be maintained on the surface of the sweepback wing, the resistance of a whole airplane can be reduced, the cruise efficiency is increased, and the consumption of fuel oil and carbon dioxide discharging can be reduced.