An oblique shock wave sweeping the turbulent boundary layer on a concave half-cylinder is employed to understand the flow in the inward-turning inlet. A series of flow deflection angles ranging from 6° to 12° are numerically examined at freestream Mach numbers ranging from 4 to 8. The results demonstrate that the swept shock wave/boundary layer interactions (SWBLI) on the concave half-cylinder deviate from the quasi-conical symmetry and the scaling law for the upstream influence line on a flat plate. A scaling law for the upstream influence line caused by the swept SWBLI on the concave half-cylinder is established, in which the effects of wall curvature are carefully considered. This new scaling law works well in a wide range of speeds.