Full application of 2D boundary layer calculations for heat transfer predictions during turbine vane design still awaits verification against relevant data. Although there are a few data sets in the literature, there is a definite need for basic vane heat transfer data under conditions that fully simulate the aerodynamic and thermal conditions of a modern turbine. Accordingly, an experiment was performed to obtain the local heat transfer distribution on a typical engine vane in an aerothermodynamic cascade facility. Heat transfer data were obtained for a range of Mach and Reynolds numbers. The cascade was closely coupled behind the facility burner so that the test included the effects of high free-stream turbulence. Turbulence data were obtained by LDV and are included.

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