Abstract: High heat flux generated by shock wave/boundary layer interaction poses a serious threat to the structural safety of aircrafts. To explore the influence of shock wave/boundary layer interaction on the heat flux distributions of hypersonic vehicles, the effects of different sweep angles and Reynolds numbers on a 34° compression corner model were investigated using infrared thermography. The results show that increasing the sweep angle helps to reduce the overall peak heat flux of the flow field, with the peak heat flux on the centerline reduced by up to one third. However, due to the influence of the bow shock wave at the trailing edge, the local heat flux of the models with small sweep angles increases, approaching the peak value of the 0° swept model. Reynolds number has a significant influence on the interference flow field of shock wave/boundary layer interaction, with higher Reynolds numbers leading to smaller separation zones and higher heat fluxes. Based on the results of this paper, the sweep angle and height parameters of the compression corner should be taken into account to avoid high heat flux or strengthen thermal protection design in those regions.