Abstract
Results of an experimental study of a supersonic combustor with a solid (continuous) and discrete (discontinuous) rear wall of the cavity are reported. The tests are performed in a short-duration wind tunnel with an attached pipeline at the entrance Mach number of 3, total temperatures of 2550–3140 K, and static pressures of 178–195 kPa. Heated kerosene is used as a fuel. Data on ignition conditions and kerosene combustion efficiency are obtained for different cavity configurations. The drag of internal elements of the combustor, which form recess stabilizers, is estimated. An overall advantage of the combustor with a discrete rear wall of the cavity over a solid rear wall is demonstrated.
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