摘要: †An assessment of the turbomachinery analysis code, APNASA, was conducted at NASA Glenn Research Center under Fundamental Aeronautics Program to determine its predictive capabilities. The geometry selected for this study Stage 35 single stage transonic compressor. A speedline generated using two turbulence models and compared experimental data 100% speed. Performance profiles several key aerodynamic parameters are survey downstream stator in report. In addition, hub leakage also modeled solutions without available data.
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