Numerical investigation is conducted on a 3.5-stage axial compressor,on which numerous experimental projects were carried out at the Institute during the last years and an experimental database was established.In the current study five on-and off-design operating points are simulated using a RANS solver and the results are compared with the measurement.The result shows that the compressor performance can be qualitatively predicted by the mixing-plane method.Better agreement is obtained for the on-design operating point.However,as the flow unsteadiness is insufficiently considered,the numerical method produces end-wall low-speed flow layers accumulated with the flow passing through the passage,which is in no good agreement with the experimental data.In the numerical simulation the rotor rows receive less work and this difference from the measurement increases with the rotational speed.In contrast,the stator rows increase the pressure more efficiently than the measurement.In the simulation the flow in the last stator row tends more to separate on the pressure side of the blade.For the operating points close to the surge line,the predicted separation is more intense than the experimental observation.But for the operating points close to the choke,the separation is suppressed. Numerical investigation is conducted on a 3.5-stage axial compressor, on which numerous experimental projects were carried out at the Institute during the last years and an experimental database was established. The current study on-and off-design operating points are simulated using a RANS solver and the results are compared with the measurement. The result shows that the compressor performance can be qualitatively predicted by the mixing-plane method. Detailed agreement is obtained for on-design operating point. However, as the flow unsteadiness is insufficiently considered, the numerical method produces an end-of-wall low-speed flow with the flow through the passage, which is in no good agreement with the experimental data. In the numerical simulation the rotor rows receive less work and this difference from the measurement increases with the rotational speed.In contrast, the stator rows increase the pressure more efficiently than the measurement. the simulati on the flow in the last stator row tends more to separate from the pressure side of the blade. For the operating points close to the surge line, the predicted separation is more intense than the experimental observation. For the operating points close to the choke , the separation is suppressed.