Model of moving solid-liquid phase change interface of a droplet following impact on a cold plate

In this study, a model of a moving solid-liquid phase change interface on the surface of an aircraft wing was constructed by combining a continuous surface tension model and a coupled dynamic boundary via the smoothed particle hydrodynamics (SPH) method. The solid-liquid phase change model was constructed using the enthalpy method as the phase change criterion. A dimensionless parameter k was defined as the ratio of the dimensionless thermal conductivity q*gas of the gas-liquid interface to the dimensionless thermal conductivity q*plate of the cold plate-liquid interface. During the initial stages of icing, the moving solid-liquid phase change interface was high in the middle and low on either side. When the change in the k′′ value reached the turning point, the heat exchange between the gas-liquid and cold plate-liquid interfaces was balanced, and the radian of the interface became very small. As the heat transfer rate at the gas-liquid interface increased, k′′ stabilised, and the moving solid-liquid phase change interface became horizontal. The model of the evolution of the moving solid-liquid phase change interface developed in this study provides an advantageous method for addressing aircraft icing problems that involve phase changes.