Organization of kerosene combustion in a model hypersonic ramjet engine

We present the results of experiments on the organization of kerosene combustion in a two-dimensional model of a hypersonic ramjet engine in conditions of external blow-out by a flow with parameters $\mathrm{M}_\infty=6$, $p^*_\infty = (53\div55)\cdot10^5$ Pa, $T^*_\infty = 1500$ K. We studied the operation of some variants of a rectangular combustion chamber with different kerosine injectors and stabilizing elements when hydrogen is used as the ignition fuel. The conditions under which kerosene burns in channels of constant area with divergence angles of 20 and 80, after hydrogen is switched off, are determined.