NUMERICAL MODELING OF SUPERSONIC-FLOW DECELERATION IN A 2-DIMENSIONALDUCT IN COMBUSTION OF WALL TANGENTIAL HYDROGEN JETS

Results are presented of a numerical modeling of the ignition and comb ustion of underexpanded turbulent hydrogen jets injected into superson ic air flow (M = 2.63) along the walls of a two-dimensional duct. Calc ulations were performed by numerical integration of reduced Navier-Sto kes equations using the method of global iterations, The kinetic mecha nism of hydrogen combustion in air involved 13 reactions. In the calcu lations the duct height was varied. In a fairly narrow duct, the stati c pressure increased with flow deceleration to subsonic velocities due to ignition and combustion. The influence of combustion on the pressu re distribution in the transverse direction is ambiguous. Initially, c ombustion increases the pressure nonuniformity (a new oblique shock wa ve occurs), while, downstream, the pressure profile is flattened out d ue to the appearance of a subsonic layer near the flame front.