Abstract
An experimental and numerical study of the flow of the organic vapor Novec 649 flow and air through an idealized vane configuration was conducted. Due to the profiling of the passage, typical pressure, and Mach number distributions for transonic and supersonic flow around a turbine blade could be established. The comparable large trailing edge radius enabled the detailed investigation of corresponding flow phenomena. Schlieren pictures and pressure distributions were experimentally obtained and compared with numerical simulations. The trailing edge flow and the transonic and supersonic shock patterns were qualitatively similar to the ones observed in the perfect gas flow. However, significant quantitative deviations were observed. The base pressure was lower in dense gas flows characterized by a fundamental derivative below unity, Γ < 1, and the corresponding loss contribution was stronger.
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