Aerodynamic performances of axial compressors are significantly affected by variation of Reynolds number in aero-engines. In the design and analysis of compressors, previous correction methods for cascades and stages have difficulties in predicting comprehensively Reynolds number effects on airfoils, matching and characteristics curves. This study proposes Re-correction models for loss, deviation angle and endwall blockage based on classical theories and cascade tests, and loss and deviation models show good agreement in test data of NACA65 and C4 cascades. Through-flow method considering Reynolds number effects is developed by integrating the correction models into a verified Streamline Curvature (SLC) tool. A three-stage axial compressor is investigated through SLC and CFD methods from design Reynolds number (Re_d = 2 × 10⁶) to low Re = 4 × 10⁴, and the numerical methods are validated with test data of characteristic curves and spanwise distributions at Re_d. With Re reduction, SLC method with correction models well predicts variation in overall performances compared with CFD calculations and Wassell’s model. Streamwise and spanwise matching such as total pressure and loss distributions in SLC predictions are basically consistent with those in CFD results at near-stall points under design and low Reynolds numbers. SLC and CFD methods share similar detections of stall risks in the third stage (Stg3), and their analyses of diffusion processes deviate to some extent due to different predictions in separated endwall flow. The correction models can be adopted to consider Reynolds number effects in through-flow design and analysis of axial compressors.