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The possibility of organizing a continuous-detonation combustion of a liquid fuel film in an annular combustor of a detonation liquid-propellant rocket engine has been demonstrated. The near-limit mode of the longitudinally pulsating “film” detonation and the continuous spinning “film” detonation modes with one and two detonation waves circulating in the annular gap of the combustor are recorded in the fire tests.
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Фролов et al. (2018) studied this question.
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