In the current study, shock-wave boundary-layer interactions of a compression cor-ner configuration are investigated for transitional and turbulent boundary-layers at Mach 6. Mean and unsteady wall pressure distributions for a range of ramp angles are obtained and demonstrate the extreme loading environment of SWBLI at hypersonic conditions. Turbulent SWBLI separation lengths are estimated using detailed focusing schlieren imagery of the interaction, while general flowfield attributes of interactions at both run conditions are assessed in the same manner. Visualizations of transitional SWBLI reveal shocklets arising during convection of boundary-layer instabilities through the separated shear-layer, which may hold implications for the amplification of such features. The presence of shocklets propagating along the separation and reattachment shocks in fully separated turbulent interactions correlates with larger instantaneous separation lengths, as measured both visually and by means of pressure sensors, and may represent ejected mass from the region of recirculating fluid at the corner.