Zheng LI, Huacheng YUAN
DOI Number: N/A
Conference number: HiSST-2025-128
The integrated configuration design of hypersonic Bump inlet requires consideration of both aerodynamic constraints generated by the aircraft forebody and strong geometric constraints within the limited space of the vehicle, while simultaneously addressing inlet flowfield shock wave system organization and aerodynamic performance. The Bump inlet design method proposed in this paper divides the integrated configuration into two parts: the Bump surface profile determined based on the forebody wave system and the internal flowpath profile based on geometric fusion. Example configuration design was conducted and validated through wind tunnel test, with design point schlieren images showing that the aircraft forebody shock wave and Bump shock wave intersect at the lip, achieving excellent integration effects. Numerical simulation further analyzed the topological structure
of the main separation regions and the background shock wave systems structure within the internal flowpath. The background wave system in the internal flowpath is primarily generated by the reflection of two families of shock waves induced by lip-reflected shocks and shoulder separation-induced shocks. By controlling the lip compression angle, the number of background shock waves in the internal flowpath was effectively reduced, resulting in a 12.35% increase in total pressure recovery coefficient at the isolator outlet and a 2.82% increase in outlet Mach number.