A core assembly for manufacturing an airfoil of a gas turbine engine, the core assembly comprising: a plurality of core bodies including hybrid skin core bodies, wherein hybrid skin core bodies provide local cooling to a single hot wall of the airfoil and cooling cavities disposed immediately adjacent to the hot wall of the airfoil, the hybrid core bodies comprising: a leading edge hybrid skin core positioned relative to the plurality of core bodies and configured to define a leading edge cavity at a leading edge of the manufactured airfoil; wherein the leading edge hybrid skin core extends from a root region toward a tip region in a radial direction, wherein the leading edge hybrid skin core extends above at least one of the plurality of core bodies to define an exit in a tip region of the manufactured airfoil, and wherein the leading edge hybrid skin core has a height-to-width ratio of about 0.8 or less, the plurality of core bodies comprising: a pressure side hybrid skin core having a first trunk and a first branch that extends from the first trunk; a suction side hybrid skin core spaced apart from the pressure side hybrid skin core; wherein the leading edge hybrid skin core is circumferentially located between the pressure side and the suction side; and wherein the core assembly is further comprising a radial flow core located between the pressure side hybrid skin core, the suction side hybrid skin core, and the leading edge, wherein the radial flow core includes: a radial core that is disposed generally parallel to at least one of the pressure side hybrid skin core, the suction side hybrid skin core, and the leading edge hybrid skin core; and wherein the radial flow core includes a radial diffusing tip flag core that extends from the radial core in a direction away from the leading edge hybrid skin core towards a trailing edge of the airfoil, wherein a radial height of the radial diffusing tip flag core increases in a direction that extends from the leading edge toward the trailing edge. a leading edge hybrid skin core positioned relative to the plurality of core bodies and configured to define a leading edge cavity at a leading edge of the manufactured airfoil; wherein the leading edge hybrid skin core extends from a root region toward a tip region in a radial direction, wherein the leading edge hybrid skin core extends above at least one of the plurality of core bodies to define an exit in a tip region of the manufactured airfoil, and wherein the leading edge hybrid skin core has a height-to-width ratio of about 0.8 or less, the plurality of core bodies comprising: a pressure side hybrid skin core having a first trunk and a first branch that extends from the first trunk; a suction side hybrid skin core spaced apart from the pressure side hybrid skin core; wherein the leading edge hybrid skin core is circumferentially located between the pressure side and the suction side; and wherein the core assembly is further comprising a radial flow core located between the pressure side hybrid skin core, the suction side hybrid skin core, and the leading edge, wherein the radial flow core includes: a radial core that is disposed generally parallel to at least one of the pressure side hybrid skin core, the suction side hybrid skin core, and the leading edge hybrid skin core; and wherein the radial flow core includes a radial diffusing tip flag core that extends from the radial core in a direction away from the leading edge hybrid skin core towards a trailing edge of the airfoil, wherein a radial height of the radial diffusing tip flag core increases in a direction that extends from the leading edge toward the trailing edge. a pressure side hybrid skin core having a first trunk and a first branch that extends from the first trunk; a suction side hybrid skin core spaced apart from the pressure side hybrid skin core; wherein the leading edge hybrid skin core is circumferentially located between the pressure side and the suction side; and wherein the core assembly is further comprising a radial flow core located between the pressure side hybrid skin core, the suction side hybrid skin core, and the leading edge, wherein the radial flow core includes: a radial core that is disposed generally parallel to at least one of the pressure side hybrid skin core, the suction side hybrid skin core, and the leading edge hybrid skin core; and wherein the radial flow core includes a radial diffusing tip flag core that extends from the radial core in a direction away from the leading edge hybrid skin core towards a trailing edge of the airfoil, wherein a radial height of the radial diffusing tip flag core increases in a direction that extends from the leading edge toward the trailing edge. a radial core that is disposed generally parallel to at least one of the pressure side hybrid skin core, the suction side hybrid skin core, and the leading edge hybrid skin core; and wherein the radial flow core includes a radial diffusing tip flag core that extends from the radial core in a direction away from the leading edge hybrid skin core towards a trailing edge of the airfoil, wherein a radial height of the radial diffusing tip flag core increases in a direction that extends from the leading edge toward the trailing edge.