The flow field of plane cascade with the blade root profile of a transonic compressor rotor was surveyed in detail at different incidences and inlet isentropic Mach numbers

and the characteristic curve of incidence and the static pressure coefficients of blade surface and end wall were gained. Results showed that the total pressure loss coefficients at the cascade outlet changed a little with different inlet isentropic Mach numbers at negative and zero incidences

and changed largely at positive incidences. With the same inlet isentropic Mach number

the blade load was high at negative and zero incidences

and decreased due to the flow separation

but the total pressure loss coefficients at the cascade outlet increased at positive incidences. With the increase of incidence

the stagger angle increased

and the total pressure loss with the minimum value of 0.034 slowed down and then up. With the increase of inlet isentropic Mach numbers

the total pressure loss coefficients at the cascade outlet increased at the same incidence.