The characteristics of flow in wake area and on blade surface had been obtained by experiment and so was the coefficient changing rule in different Reynolds number conditions.The experimental results show that with the Reynolds number decreasing,great changes happen in wake area and to Mach number distribution on blade surface.At the same time,the loss coefficient of cascade increasing rapidly.At low Reynolds number,the turning Reynolds number of this profile is bigger with the inlet Mach number incresaing.The main reason for loss coefficient increasing and great changes in wake area is the flow separation on suction surface in very low Reynolds number condition.
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凌代军,王晖,马昌友.低雷诺数亚声速扩压平面叶栅试验[J].航空动力学报,2013,28(1):171~179. LING Dai-jun, WANG Hui, MA Chang-you. Subsonic compressor plane cascade experiment at low Reynolds number[J]. Journal Of Aerospace Power,2013,28(1):171-179.