Abstract
A closed mathematical model of continuous spin detonation of a hydrogen-air mixture in a quasi-three-dimensional unsteady gas-dynamic formulation is developed. The model takes into account the reverse effect of oscillatory processes in the combustor on the injection system. Numerical simulations are performed for the geometric parameters of the flow-type annular combustor 306 mm in diameter used in experiments. The one-wave, two-wave, and three-wave regimes of continuous spin detonation for varied flow rates of the mixture are calculated, and the flow structure is analyzed.
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