Abstract: A turbine blade for a gas turbine engine, the turbine blade having: an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a radial direction to a tip; and wherein the exterior airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in at least one of Tables 1-3, and wherein the set of Cartesian coordinates in Tables 1-3 are offset from a center point of an inner diameter edge of a forward root face of a root of the turbine blade by offsets of Table 4 to provide the exterior airfoil surface at a span location.