In this article, a compressor rotor blade is numerically modeled and solved by a CFD code. A stepped blade with higher aerodynamic characteristics is used to investigate unstable zone and improve operational limit and compressor stall. To validate numerical data original test case compared with experimental measurements. In this study, several locations of step on suction side of blades are tried, finally the results are compared with the case with no step on blades. It is shown that, by moving the step towards the leading edge, surge is delayed due to the reattachment of flow after the step. Efficiency is also decreased but lower than previous case.