Flow inside the isolator of a scramjet engine is likely to be in thermal non-equilibrium due to successive shock-based compressions and expansions. Given the short flow-through timescales in such engines, the flow might not reach equilibrium even in the fuel injection region. Since the distribution of energy in the internal modes affects chemical reactions, non-equilibrium has been shown to have significant impact on ignition and flame stabilization. In this study, detailed numerical simulation of a supersonic turbulent channel flow coupled with a multi-temperature model is used to quantify the impact of thermodynamic non-equilibrium on the shock train structure inside the isolator and the flow characteristics at the outlet.
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