Abstract
Several kinetic models of hydrogen oxidization are compared for the purpose of selecting the reaction mechanism to describe the chemical interaction in numerically modeling the detonation combustion of a hydrogen-airmixture. Within the framework of the chosen kinetic model the possibility of stabilizing a detonation wave in a stoichiometric hydrogen-airmixture arriving in a plane channel at a supersonic velocity is discussed. For certain inflow Mach numbers a method for determining the shape of the channel, in which a stabilized detonation wave can be formed without energy supply, is proposed. In the case of the M0 = 5.5 combustible mixture flow past a semi-infinite symmetric plane body aligned with the flow the structure of the detached detonation wave stabilized ahead of the obstacle is studied.
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Original Russian Text © T.A. Zhuravskaya, V.A. Levin, 2015, published in Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, 2015, Vol. 50, No. 2, pp. 117–128.
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Zhuravskaya, T.A., Levin, V.A. Stabilization of detonation combustion of a high-velocity combustible gas mixture flow in a plane channel. Fluid Dyn 50, 283–293 (2015). https://doi.org/10.1134/S001546281502012X
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DOI: https://doi.org/10.1134/S001546281502012X