Researchers at NASA GRC conducted an experimental investigation of the flow physics of turbine film cooling by obtaining detailed mean and fluctuating velocity and temperature surveys in the turbulent jet flow field behind a row of large scale film cooling holes. Surface heat transfer film effectiveness and turbulent heat flux values were also determined. Measurements were made in the NASA ERB SW-6 test facility, which consists of an 8.15-inch square open-inlet wind tunnel with a temperature-controlled secondary flow system. The test plate consisted of a three-hole array of film cooling holes that were fed from a plenum of different temperature. The model geometry was scaled up roughly 30 times of typical turbine film cooling size to enable high spatial resolution measurements near the film coolant hole. High-resolution survey data was taken along a centerline streamwise plane behind the hole as well as at various cross-sectional planes behind the hole at two blowing ratios. Mean and fluctuating flow field velocity and temperature measurements were made using various thin wire anemometry probes; surface temperature and heat transfer measurements were made employing liquid crystal and infrared imaging techniques. In addition, a two-plane particle image velocimetry (PIV) technique was performed downstream of the coolant holes to compare with the velocity and turbulent quantities measured by the hotwire probe.