A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, at least some of the plurality of cooling holes being located on a suction side of an airfoil of the turbine blade and in fluid communication with an internal cavity of the turbine blade; and wherein the at least some of the plurality of cooling holes are located in the airfoil according to the coordinates of Tables 1 and/or 2.