Experimental investigations of aerodynamics performance of aspirate subsonic compressor cascade

Based on the experimental platform-subsonic cascade wind tunnel,the parameters such as cascade suction surface,static pressure distribution on the surface of the cascade and cascade tail,were tested under different Mach numbers,incidence angles and suction flow rates.The results show that,the boundary layer suction could reduce the cascade's total pressure losses,decrease the deviation angles and improve the aerodynamics performance of cascade.With the appropriate suction slot location and suction flow rate,the internal flow of cascade will become more rational.