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Numerical modeling of detonation combustion of hydrogen-air mixtures in a convergent-divergent nozzle

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Abstract

The flow of igniting hydrogen-air mixtures entering an axisymmetric convergent-divergent nozzle at a supersonic velocity is considered. A possibility of stabilizing detonation combustion is numerically investigated at different freestream Mach numbers with account for nonuniform distribution of hydrogen concentration at the nozzle entry. The investigation is performed on the basis of the two-dimensional gasdynamic Euler equations for a multicomponent reacting gas. A detailed model of chemical reactions is used. The calculated thrust is compared with the drag of a conical housing containing the supersonic nozzle considered.

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Authors
  1. Yu. V. Tunik
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Additional information

Original Russian Text © Yu.V. Tunik, 2010, published in Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, 2010, Vol. 45, No. 2, pp. 107–114.

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Tunik, Y.V. Numerical modeling of detonation combustion of hydrogen-air mixtures in a convergent-divergent nozzle. Fluid Dyn 45, 264–270 (2010). https://doi.org/10.1134/S0015462810020110

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  • DOI: https://doi.org/10.1134/S0015462810020110

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