Abstract
The flow mixing mechanism between sonic fuel jet and supersonic mixed inflow is one of the key technologies in rocket-based combined cycle engines. In this study, the flow mechanism of different supersonic airflow conditions on the flow field is discussed. The variable parameters are the Mach number and total pressure of the airflow. The three-dimensional Reynolds-averaged Navier-Stokes equations, two equations of the shear stress transport k-ω turbulence model, and the Eddy-dissipation concept reaction model are adopted to evaluate the flow field structure. The results reveal that the shear layer between the airflow and the rocket gases gradually slopes downward with the increase of Mach number. The bow shock induced by the jet develops to the upper wall and cuts off the shear layer vortex. Additionally, as the Mach number of the airflow decreases, the mixing and combustion efficiencies gradually increase. The Mach number has a slight influence on the penetration depth. Furthermore, when the total pressure of the airflow increases, the penetration depth and mixing efficiency sharply increase.
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