Countless combinations of sizes and shapes of the flow path could ensure the specified flow rate and pressure ratio of the axial compressor stage. Programs based on the mathematical models are an effective tool in initial design and preliminary selection of the optimal option. The RROK-GPD-22 software program is briefly being described, it solves the problem on the basis of the pressure loss model and deflection capacity of the A. Komarov lattice, theoretic rigorous calculation of oblique and direct shocks, as well as empirical equations and coefficients. Models were checked by comparison with data on the Rotor 37 NASA test stage. Stages were calculated with different ratio of the cross-sectional area at the outlet of the impeller to that at its inlet and stages with the hub-tip ratios of 0.400 ... 0.728 with different swirl at the impeller inlet. Results are provided in determining the hub-tip ratio influence on the efficiency, pressure ratio and specific stage performance.