Numerical Simulations on a Liquid Jet in Supersonic Crossflow using a Homogeneous Mixture Model with AMR

Abstract

The combustion efficiency of an air intake propulsion system using liquid fuel in supersonic crossflow is sensitive to fuel spray characteristics, such as atomization and fuel-air mixture. Using liquid jets in crossflow is a general method to improve fuel spray and air-fuel mixing characteristics. The atomization process has a strong correlation with various physical parameters, such as turbulence intensity, mixing conditions, and geometric characteristics. In this study, a numerical analysis was conducted to analyze the process of liquid jet breakup and mixing in supersonic crossflow. Homogeneous mixture model (HMM), Novel-abel stiffened gas (NASG) state equation, adaptive mesh refinement (AMR) technique, and Eulerian-Lagrangian (EL) transformation are applied. The calculation condition involves injecting water liquid jet at a supersonic crossflow, Mach number of 2.0. The interaction between the crossflow and liquid jet leads to liquid surface instability and ligament process separated from the liquid column. Numerical simulations show that the penetration depth, surface waves caused by instability, distance between the shock waves and the liquid jet, and the length of the liquid jet breakup are fairly comparable to experimental results.