This study uses radial equilibrium and fundamental design methodologies to design a single-stage subsonic axial flow compressor for aerospace applications. The compressor is designed to achieve specified mass flow rate, rotational speed, and pressure ratio requirements. The rotor and stator blades are segmented into eleven sections to ensure smooth variation of parameters, and C4-type airfoil profiles are utilized for blade design. The radial design approach results in a 36.6% higher blade deflection angle (Δβ) at the hub compared to the fundamental design, leading to increased twist at the hub section. The radial design shows a more rapid increase in aerodynamic loading along the blade span, while the fundamental design demonstrates a more balanced loading distribution. Diffusion factor (DF) distribution in the radial design enhances stability and efficiency, whereas the fundamental design focuses on maximizing pressure rise with careful consideration of aerodynamic loading and stability. Furthermore, the stator blade analysis reveals a uniform diffusion factor (0.37–0.43) with the fundamental approach. The degree of reaction (DoR) varies between 0.87 and 0.22 for radial design and 0.64 and 0.27 for fundamental design, indicating distinct aerodynamic characteristics.