Supersonic combustion in liquid jet flows with sharp interface method, evaporation model, and flamelet model

The present study provides a numerical method designed to simulate the supersonic combustion of liquid jet flow. The compressibility of the gas and the incompressibility of the liquid are considered. Based on the mass, momentum, and energy conservation equations, the heat and mass transfer at the gas-liquid interface are calculated. The motion of the sharp interface between the gas and liquid is simulated using the volume-of-fluid method. The ghost fluid method solves the discretization problem of the interface with velocity jump conditions. A Harten-Lax-van Leer-contact (HLLC) approximate Riemann solver is used to simulate supersonic flow. The unsteady flamelet/progress variable model is used to simulate combustion. The method is employed to simulate the atomization and combustion of a fuel jet in supersonic airflow. Due to droplet evaporation, a large area of low temperature is present near the leeward side of the liquid transverse jet. Therefore, it will be difficult to ignite the liquid fuel in a short time period.