V.B. Betelin

TL;DR: In this paper, the authors investigate problems of numerical simulations precision and stochastic errors accumulation in solving problems of detonation or deflagration combustion of gas mixtures in rocket engines.

TL;DR: In this article, the results of computer code developing, verification and validation, making it possible to simulate unsteady processes of ignition and combustion of hydrogen fuel in rocket engines are developed.

TL;DR: In this article, the non-equilibrium effects in droplets atomization and phase transitions are taken into account in describing thermal and mechanical interaction of droplets with streaming flows, and the behavior of individual droplets in a heated air flow allowed to distinguish two scenarios for droplet heating and evaporation.

TL;DR: In this article, a modified ka-omega turbulence model is used to simulate flame acceleration in the Shchelkin spiral section of the system, and the results of numerical simulations were compared with experiments, which had been performed in the same size detonation chamber and turbulent spiral ring section, and with theoretical data on the Chapman-Jouguet detonation parameters.

TL;DR: In this paper, a mathematical model is developed accounting for the peculiarities of diffusion combustion of fuel in the flow of oxidant, which is composed of oxygen-nitrogen mixture.