Experimental investigation of shock–shock interactions with variable inflow Mach number

Abstract Experiments on shock–shock interactions were conducted in a transonic–supersonic wind tunnel with variable free-stream Mach number functionality. Transition between the regular interaction (RI) and (MI) was induced by variation of free-steam for fixed geometry, as opposed to most previous studies where shock generator angles are varied at constant number. In this paper, we present systematic flow-based post-processing methodology schlieren data that enables an accurate tracking evolving system including precise reproducible detection RI $$\rightleftarrows $$ ? MI transition. line experimental dealing noisy environments, transition hysteresis not observed. However, show establishing values flow deflections besides is crucial achieve agreement von Neumann criterion, since measured deviated significantly, up $$1.2^{\circ }$$ 1 . 2 ? , from nominal wedge angles. We also report study focusing focal plane supported image processing providing insights into three-dimensional side-wall effects integrated images.