Effect of the configuration of the rear wall of the cavity on combustion in a supersonic combustion chamber

Results of an experimental study of a supersonic combustion chamber 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 input 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 combustion chamber, which form recess stabilizers, is estimated. An overall advantage of the combustion chamber with a discrete rear wall of the cavity over a solid rear wall is demonstrated.