Flow Field Computational Analysis in a Solid Fuel Scramjet Combustor

Abstract

According to the domestic and foreign institutions of solid fuel scramjet experimental data, adopt the numerical simulation method, design to construct the numerical model of the combustion chamber, using RNG k- turbulence model and eddy dissipation combustion model, simulation combustor working condition, analysis of the combustion chamber flow field data, concluded that the combustion phenomenon occurs mainly in the center of the flow field area. At the entrance of the combustion chamber can produce normal shock. The cavity can reduce the air velocity and it can guarantee the stability of the flame burning, and that to calculate the specific impulse is 126N·s/kg.