This paper focuses on the compressor cascade experiment and numerical simulation at order 105 Reynolds number. A cascade tunnel simulated low Reynolds number condition under high subsonic speed. In a series of experiments (Re = 0.9 × 105∼5.0 × 105), oil flow visualization tests were used to indicate boundary layer development of the cascade surface. The results show that the performance of cascades deteriorates rapidly when the Reynolds number decreases to a certain extent. Comparison of results between the tests and calculations demonstrates that the real cascade experimental environment must be considered, such as the effect of the end wall. Flow separation and transition can be predicted accurately by using SST turbulence and Gamma transition models. Through modifying parameters of the Gamma transition model, the profile Mach number distribution in numerical simulations exhibits good agreement with experiments. Response surface methodology was adopted for the design process to minimize the total pressure loss of cascades at the design point. In addition, the optimized result has little negative effect on the high Reynolds number region.

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