This paper presents a new design and analysis tool that is developed to be employed during the design process of axial flow compressors. The tool chain implemented by this design tool consists of five parts: a mean-line design tool, followed by a blade geometry parametrization tool. Then 3D blade geometry is created, next a high quality structured mesh is generated and completed by Computational Fluid Dynamics (CFD) solution. All components employed in the new tool are either new developments, or achieved by utilization of in-house solvers. Design process for a multistage axial flow compressor starts with the 1-D mean line design phase, followed by 2D design of the blade by employing radial equilibrium theory. 3D blade geometry is constructed by the mapping and stacking operations of the 2D blade cross-sections calculated and generated at the geometry parametrization tool by using geometric parameters of blade angles, chord lengths, blade thickness distributions, hub and shroud curves. These cross sections are defined with non-uniform rational B-spline (NURBS) curves for optimization objectives. In the solution part, an in-house developed multiblock structured mesh generation code is restructured to automatically generate mesh around the 3D blade. 3D CFD analyses are performed by an in-house solver on this grid. The design and solution cycle is validated by using NASA Rotor-37 compressor rotor test case. A new rotor blade is achieved with similar pressure-ratio with Rotor-37.