The metal angle distribution of mean camber line has an important effect on the isentropic mach number distribution of compressor blade surface. In order to compare the flow characteristics of different compressor blade profiles， the aerodynamic characteristics of two transonic blade with different metal angle distribution under different inflow conditions are numerically and experimentally studied. The results show that： At the design point， compared with the front-loaded blade， the metal angle distribution blade with front loading and uniform loading has a fuller isentropic Mach number distribution on the blade surface， which can eliminate the local supersonic zone. Secondly， this kind of blade delays the instability position of the vortex layer on the suction surface， and weakens the coupling of the suction separation vortex and the end wall separation vortex. The corner separation is suppressed， and the flow in the corner area is improved. The average total pressure loss coefficient is reduced by 8.2%. Finally， the aerodynamic characteristics of the cascade under off-design conditions are analyzed. With the decrease of the inflow Mach number， the difference of the loss of the two metal anger distribution blades gradually decreases， and both have good aerodynamic performance.