Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : September 08, 2024 - September 11, 2024
Ice accretion on an aircraft occurs when supercooled droplets in a cloud impinge on a body. Aircraft icing threatens navigation safety as icing on a wing deteriorates aerodynamic performance. Although it is required to predict icing accurately, estimating ice accretion is challenging due to its multi-physics nature. In addition, under supercooled large droplet (SLD) conditions, where the droplets’ diameter is over 40 μm, the behavior of impinging droplets becomes more complex. In this study, numerical simulation for SLD icing using coupling scheme of grid- and particle-based methods were conducted. The numerical scheme for heat transfer treatment in the particle-based method was improved to reproduce the solidification process of droplets. In addition, highly resolving simulation was realized by applying a computational cost reduction method. As a result, the ice shape apart from the leading edge backward was reproduced with higher resolution than in our previous study. Furthermore, the catalyst of the unique ice shape in SLD icing (i.e. feather shape) was observed. The present simulation scheme will provide a more useful prediction for SLD icing in the designing phase of an aircraft.
