The annular bowed compressor cascads with large camber angle under different inlet boundary layers thicknesses were investigated experimentally and numerically under low-speed condition.The effects of bowed blade on aerodynamic performance of compressor cascade were analyzed under different inlet boundary layer thicknesses.The results show that

when the inlet boundary layer is getting thinner

the aerodynamic performance of cascades improves under most flow conditions.However

the total loss will rise sharply if bowed blade with bigger incidences is adopted in the cascade with larger camber angle when the bowed angle is bigger.