A three-dimensional numerical investigation was performed of the ignition processes and scaling capabilities of a radical farming scramjet. The CFD computations presented in this study validated a previous set of experiments conducted in the Australian National University T3 shock tube. The first set of computations was performed to state the ignition and combustion efficiency of the radical farming engine concept, various total enthalpies, ranging from 3.4MJ/kg to 6.29MJ/kg, were studied. For the experiments, a nominal Mach number of 6 was chosen and subsequently the equivalence ratio was set to φ = 1.4 and kept constant.
The flow topologies of gas and liquid injection into hypersonic crossflow are compared with the flow topology around 3D rigid obstacles in hypersonic flow. Experimental techniques such as oil flow visualization, infrared thermography, sublimation technique and high speed Schlieren photography are applied for a Mach 6 crossing flow on a flat plate. The shock system and the vortex system are visualized and discussed for all cases. Pressure ratio for gas injection, momentum flux ratio for liquid injection and Reynolds number for 3D obstacles are taken into consideration. The effects of non-dimensional numbers on the flow topologies are analyzed. Similarities and differences among different topologies are explained by studying the vortical aerodynamics, making use of CFD simulations.
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