An airfoil for a gas turbine engine , comprising: an airfoil body having a pressure side and a suction side that each radially extend between a first radial boundary end and a second radial boundary end and each axially extend between a leading edge and a trailing edge , the airfoil body defining: a plurality of first skin core passages disposed proximate the suction side and radially extending from the first radial boundary end towards the second radial boundary end, and a plurality of second skin core passages that radially extend from the first radial boundary end toward the second radial boundary end and circumferentially extend towards the suction side proximate the second radial boundary end; a main body core passage ; a first skin core inlet passage connected to the plurality of first skin core passages; and a second skin core inlet passage connected to the plurality of second skin core passages, characterised in that the second skin core inlet passage is circumferentially disposed between the first skin core inlet passage and the main body core passage such that cooling air within the second skin core inlet passage is thermally shielded by at least one of the main body core passage and the first skin core inlet passage. an airfoil body having a pressure side and a suction side that each radially extend between a first radial boundary end and a second radial boundary end and each axially extend between a leading edge and a trailing edge , the airfoil body defining: a plurality of first skin core passages disposed proximate the suction side and radially extending from the first radial boundary end towards the second radial boundary end, and a plurality of second skin core passages that radially extend from the first radial boundary end toward the second radial boundary end and circumferentially extend towards the suction side proximate the second radial boundary end; a main body core passage ; a first skin core inlet passage connected to the plurality of first skin core passages; and a second skin core inlet passage connected to the plurality of second skin core passages, characterised in that the second skin core inlet passage is circumferentially disposed between the first skin core inlet passage and the main body core passage such that cooling air within the second skin core inlet passage is thermally shielded by at least one of the main body core passage and the first skin core inlet passage. a plurality of first skin core passages disposed proximate the suction side and radially extending from the first radial boundary end towards the second radial boundary end, and a plurality of second skin core passages that radially extend from the first radial boundary end toward the second radial boundary end and circumferentially extend towards the suction side proximate the second radial boundary end; a main body core passage ; a first skin core inlet passage connected to the plurality of first skin core passages; and a second skin core inlet passage connected to the plurality of second skin core passages, characterised in that the second skin core inlet passage is circumferentially disposed between the first skin core inlet passage and the main body core passage such that cooling air within the second skin core inlet passage is thermally shielded by at least one of the main body core passage and the first skin core inlet passage. <EOS>