Modern gas turbine airfoils are subject to gas temperatures greater than 3000 degrees F that exceed the thermal limits of the airfoil material.Therefore, the airfoils have to be actively cooled, and both internal cooling and external cooling strategies have to be utilized for the first stage airfoils.The cooling air, which is bled off the compressor stage into the internal airfoil passages, is routed externally through inclined holes drilled on the airfoil surface.The air exiting these inclined holes is expected to provide a protective coolant film on the material surface, and to therefore prevent the surface from being exposed to the deleterious effects of the hot crossflow.