Aeroheating of scramjet inlet cowl lip was investigated using numerical simulation method.Three cases were investigated depending on cowl lip position relative to forebody shock

and computational fluid dynamics(CFD) method was used to calculate blunt bow shock flow and simulate shock/shock interaction flow field.The results were validated with experiments in reference

showing that the inlet leading edge always bears more serious aerothermal challenge than forebody nose.Computation shows that it is shock/shock interaction and compressing supersonic flow post forebody shock that increase cowl lip heat transfer for hypersonic vehicle with airbreathing scramjet.This must be fully considered in the thermal protection and structure design.