Abstract: An investigation was conducted in an effort to verify the aerodynamic characteristics. Of a two-stage axial-flow compressor with inlet hub-tip ratio 0.45 and have a good command of the technique of compressor performance testing. The performance parameters of the compressor were measured a;, relative equivalent speed nnp=0.546,0.766, 0.876 and 1.00.The compressor surging in low speed range had being observed. The test results show that the total pressure ratio was measured approaching to the theoretical calculation and at the mean radius the velocity diagram is basically in accord with that designed, only that the adiabatic efficiency of this compressor experimentally measured differs from the design value due to ununiform temperature field and calculating method available in which the temperature rises are incorporated.