Shock-wave/boundary-layer interactions (SWBLI) strongly influence the aerodynamic
behaviour of many aerospace, propulsion and transportation systems. They have therefore
been studied intensively—with different methods, configurations, and test facilities. Regions
of favourable pressure gradient are often placed downstream of the SWBLI region., eg to
prevent wind-tunnel blockage. To be able to better understand their effect and compare
cases from varying sources, a joint experimental–numerical study of a supersonic …