Much attention is paid to improving the methods of gas-dynamic design of axial compressors. Variants of the supersonic stage of an axial compressor with different hub ratios and pre-swirling of the flow were subjected to computational analysis. All variants have the same mass flow rate, flow coefficient and outlet angles of the blades at the hub diameter. The analysis was carried out according to the program of primary design in a quasi-three-dimensional setting. The graphical representation shows the quantitative results of the influence of the hub ratio and of the flow swirl on the efficiency, the loading factor and the pressure ratio of the stage. An analysis of the flow structure and velocity triangles explains the reasons for the change in efficiency and loading factor. The dependences of the efficiency and the loading factor on the hub ratio and flow swirl are approximated by a system of algebraic equations.