The high-load compressor plays an important role in further improving the performance of aero-engine. However, the complex shock waves in the cascade channel also bring more aerodynamic losses. This paper proposes a supersonic compressor cascade modeling method based on the theory of unique inlet flow angle, and the aerodynamic design and optimization of a cascade with inlet Mach number 1.85 are studied by combining the numerical optimization method and planar cascade experiment. The results show that pressure increase can be achieved by multiple shock waves which are obtained by the reflection of the leading edge detached shock wave in the initial supersonic cascade channel at the design point, which verifies the feasibility of the design method. After optimization, the aerodynamic performance of the cascade has been improved to different degrees at the design point and off-design point. When the static pressure ratio is 3.285, the total pressure recovery coefficient reaches 86.82% at the design point, which is on the advanced level of the same type of cascade. The experimental results of planar cascade schlieren and surface pressure measurement also verify the correctness of the simulation method, which provides useful references for the subsequent compressor design.
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