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.