Abstract
A two-dimensional unsteady mathematical model of a continuous spinning detonation wave in a supersonic incoming flow in an annular combustor is formulated. The wave dynamics in a combustor filled by a gaseous hydrogen-oxygen mixture is studied. The possibility of continuous spin detonation with a supersonic flow velocity at the diffuser entrance is demonstrated numerically for the first time; the structure of transverse detonation waves and the range of their existence depending on the Mach number are studied.
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Translated from Fizika Goreniya i Vzryva, Vol. 44, No. 6, pp. 83–91, November–December, 2008.
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Zhdan, S.A. Mathematical model of continuous detonation in an annular combustor with a supersonic flow velocity. Combust Explos Shock Waves 44, 690–697 (2008). https://doi.org/10.1007/s10573-008-0104-z
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DOI: https://doi.org/10.1007/s10573-008-0104-z