Effect of thermal nonequilibrium on the shock interaction mechanism for carbon dioxide mixtures on double-wedge geometries

The effect of thermal nonequilibrium on shock interactions carbon dioxide (CO 2 ) hypersonic flows is investigated. Given the relatively low characteristic vibrational temperature CO molecule, it expected that excited modes play a significant role in physics shock/shock and shock/boundary layer interactions. interference mechanism resulting from -dominated flow over different double-wedge geometries investigated by numerically solving Navier–Stokes equations within framework two-temperature model considers translational energy–vibrational energy transfer. To assess impact relaxation, comparative assessment patterns obtained with three thermo-physical models presented, pattern being compared to thermally perfect ideal gas ones. Results show increasing aft angle significantly enlarges separated region compression corner generates numerous secondary waves shear layers. Peaks heat flux pressure occur along surface due boundary reattachment downstream corner, except for case higher angle, which results largest peaks impingement. Different assumptions excitation are shown largely influence size recirculation bubble interaction mechanism, loads. more transferred mode, lower post-shock temperatures obtained, tends reduce density, leading weaker characterized delayed onsets separation, reduced separation regions, smaller standoff distances.