In this study numerically and experimentally was investigated the effects of bumps on the compression performance. The first bump, Mod-1, has a soft inlet and soft outlet. Mod-2 is designed with similar characteristics but twice as long. The numerical analysis, conducted at 1.8 Ma for two cases, revealed that the Mod-2 bump is more effective than the Mod-1 in mitigating disturbance factors such as flow separation, reverse flow movement, and vortex zones in the duct. By examining the total pressure and the distortion coefficient DC60 at the engine surface (AIP) for the two cases with cross sections taken from the duct, it was found that Mod-2 is 9% more efficient than Mod-1. To illustrate the accuracy of the numerical analysis, two different bump models were produced and tested in a supersonic wind tunnel. In addition, the relationship between cone angle and cone shock was established numerically and experimentally with the obtained results.