In this study, a new bump configuration that can be applied to hypersonic inlets to improve aerodynamic performances, is proposed. The new design contains bump-shaped surfaces only near the sidewalls and not in the center, unlike conventional designs. The performance parameters of the designed bump inlet are evaluated by numerical simulations. The results reveal that the bump exhibits good displacement capability for the boundary layer, which reaches an average thickness of 5.53 mm, showing a 5.6% decrease compared with a traditional bump. Additionally, because the proposed configuration does not contain a central bump-shaped surface, the unwanted total pressure loss and drag are avoided, increasing the pressure recovery by 5.0% and reducing the drag by 2.5%. Finally, a mass flow correction is conducted, which increases the mass flow ratio to 0.997.