The film cooling effectiveness distributions on the leading edge and the pressure side of a turbine vane are tested using pressure sensitive paint (PSP) for various blowing ratios and density ratios. A uniform effectiveness distribution is obtained along the leading edge by proper arrangement of the film cooling holes. The film cooling flow distribution on the pressure side from the leading edge injections is related to the blowing ratios with higher blowing ratios given wider coverage. The coolant injections on the pressure side are supplied independently for each row of holes to conveniently and accurately control the local flow parameters. This paper presents the film cooling efficiencies for each injection row for different blowing ratios and density ratios. The film cooling performance on the pressure side is most strongly related to the blowing ratio since the injected coolant remains in good contact with the wall with this hole shape arrangement. When the coolant is injected through all the holes together, the film cooling effectiveness downstream can be predicted using Shettle superposition.