A combination of a leading edge for a wing of an aircraft and an anti-icing system that is arranged to blow heated air to a curved inner surface of the leading edge , the anti-icing system comprising: a piccolo tube that includes a flow path through which the heated air can flow in a longitudinal direction from a rear end to a front end, and a plurality of ejection holes provided along the longitudinal direction to make the flow path communicate with an outside and to eject the heated air as jet flows toward the inner surface of the leading edge ; and a supply source that is arranged to supply the heated air toward the piccolo tube , wherein the plurality of ejection holes of the piccolo tube are straightly arranged in only two lines consisting of a first ejection hole line L1 and a second ejection hole line L2, the first ejection hole line L1 being disposed on a relatively upper side and the second ejection hole line L2 being disposed on a lower side of the first ejection hole line L1 such that the jet flows of the heated air ejected from the ejection holes of the first ejection hole line L1 generate, in operation, a first line of blown points on the inner surface of the leading edge corresponding to an outside airflow stagnation point (P1) on an upper side of the leading edge , such that the jet flows of the heated air ejected from the ejection holes of the second ejection hole line L2 generate, in operation, a second line of blown points on the inner surface of the leading edge corresponding to an outside airflow stagnation point (P2) on a lower side of the leading edge , and such that no jet flows of the heated air are ejected to blown points on the inner surface of the leading edge between the first and second lines of blown points, and wherein the outside airflow stagnation points (P1,P2) on the upper and lower sides of the leading edge are virtually determined based on a cross-sectional surface of the wing and a specific assumed angle of attack of the aircraft. a piccolo tube that includes a flow path through which the heated air can flow in a longitudinal direction from a rear end to a front end, and a plurality of ejection holes provided along the longitudinal direction to make the flow path communicate with an outside and to eject the heated air as jet flows toward the inner surface of the leading edge ; and a supply source that is arranged to supply the heated air toward the piccolo tube , wherein the plurality of ejection holes of the piccolo tube are straightly arranged in only two lines consisting of a first ejection hole line L1 and a second ejection hole line L2, the first ejection hole line L1 being disposed on a relatively upper side and the second ejection hole line L2 being disposed on a lower side of the first ejection hole line L1 such that the jet flows of the heated air ejected from the ejection holes of the first ejection hole line L1 generate, in operation, a first line of blown points on the inner surface of the leading edge corresponding to an outside airflow stagnation point (P1) on an upper side of the leading edge , such that the jet flows of the heated air ejected from the ejection holes of the second ejection hole line L2 generate, in operation, a second line of blown points on the inner surface of the leading edge corresponding to an outside airflow stagnation point (P2) on a lower side of the leading edge , and such that no jet flows of the heated air are ejected to blown points on the inner surface of the leading edge between the first and second lines of blown points, and wherein the outside airflow stagnation points (P1,P2) on the upper and lower sides of the leading edge are virtually determined based on a cross-sectional surface of the wing and a specific assumed angle of attack of the aircraft. <EOS>