Numerical simulations on RBCC engine in Scramjet/rocket mode

Under the conditions of low dynamic pressure, high velocity and high flight altitude, numerical simulations were carried out to analyze the flowfield characteristics of rocket-based combined cycle (RBCC) engine in the Scramjet/rocket mode, which was composed of a combustor matched with an appropriate inlet and exhaust system. The effects of the variations of the strut-rocket mass flowrate at the exit of the nozzle on the combustion flow were also investigated. The results show that in Scramjet/rocket mode, the operation of strut-rocket can enhance the mixing and combustion between fuel and air, realize the steady operation of engine, while promoting the thrust performance. The total thrust of the engine increases gradually with the increment of the strut-rocket mass flowrate, which is proportional to the rocket mass flowrate approximately. The flow condition in the combustor develops towards the flow dominated by supersonic, and the resistance pressure ability of the inlet improves as the rocket flowrate increases.