Numerical simulation of efflux of a supersonic multicomponent chemical reacting rocket engine jet

1Timoshenko, VI, 1Deshko, HYe.
1Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine, Dnipropetrovsk, Ukraine
Kosm. nauka tehnol. 2017, 23 ;(6):03-12
Section: Space Energy, Power and Propulsion
Publication Language: Russian
Numerical simulation of non-equilibrium efflux of a supersonic combustion products jet with water droplets adding is carried out on the basis of a two-speed and a two-temperature model of a continuous medium with using the marching calculation method. The afterburning mechanism of combustion products in air oxygen is modeled by the kinetic model, which includes 11 elementary chemical reactions. The simplest model for evaporation of water droplets is considered. The influence of components afterburning and water adding to the jet’s body on the change in jet thermal characteristics is numerically investigated.
Keywords: combustion kinetics, marching calculation methods, nonequilibrium flow, parabolic Navier-Stokes equations, viscous two-phase сombustion products jet