An aerodynamic design principle for subsonic axial-flow compressor with low reaction based on enhanced axial velocity was proposed to solve the internal flow problems when the stage load was further enhanced by increasing the turning angle of the flow in the rotor. The mutual interactions between each aerodynamic parameter were analyzed based on this aerodynamic design principle

and a verification stage had been designed. The three-dimensional viscous numerical simulation results show that a compressor design of stage pressure ratio of 1.5 with efficiency of 92.5% at tip tangential speed of 213m/s has been attained.