The invention relates to a three-dimensional blade modeling method for a multistage axial flow compressor based on an end region boundary layer. The three-dimensional blade modeling method is characterized by comprising the following steps of step 1, analyzing the meridian through-flow performance of the prototype multistage axial flow compressor; secondly, extracting the radial gradient of the meridian velocity profile through the through-flow performance in the first step, so that the boundary of a boundary layer is determined, and calculating the displacement thicknesses of the wheel flangeand the boundary layer of the wheel hub side; and step 3, determining initial three-dimensional blade modeling parameters, determining the bending height of the three-dimensional blade according to the relative blade height of the boundary of the corresponding side boundary layer, determining the bending angle of the three-dimensional blade according to the displacement thickness of the corresponding side boundary layer, and forming three-dimensional deformation of a stacking line according to the bending height and the bending angle to obtain the three-dimensional modeling of the blade. Theintegrated modeling design of the three-dimensional blade of the multistage axial flow compressor is realized, the multistage influence of the multistage axial flow compressor is considered, and the flow efficiency of the compressor is improved while the stable work of the compressor is ensured.