Control of thrust characteristics of a scramjet combustor with vibrational combustion using acoustic resonators

The effect of a resonator on the thrust characteristics of a scramjet combustor with vibrational combustion of hydrogen is studied experimentally. A cylindrical tube with a confuser entrance was used as a combustion chamber. The centerline of the resonator is perpendicular to the combustor axis. It is shown that the thrust characteristics of the combustor depend on the resonator position relative to the combustor and on the linear dimensions of the resonator.