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ISSN Online: 2379-1748

ISBN Flash Drive: 978-1-56700-472-4

ISBN Online: 978-1-56700-471-7

3rd Thermal and Fluids Engineering Conference (TFEC)
March, 4–7, 2018, Fort Lauderdale, FL, USA

ICING STUDY OF SUPER COOLED WATER DROPLET IMPINGING ON AIRFOIL USING E-MPS METHODD

Get access (open in a dialog) pages 1185-1191
DOI: 10.1615/TFEC2018.rhe.021654

Abstract

Ice accretion on an aircraft can cause serious problems or it can drastically decrease the aerodynamic performance. Therefore, prediction of the accreted ice shape by numerical simulations is of importance in the development of aircrafts and jet engines. It is difficult to reproduce the ice shape by means of numerical simulations based on the Eulerian approach, since the icing forms complicated ice shapes such as horn and feather. In the present study, instead of the Eulerian method, an explicit-moving method was employed and the method is one of the numerical methods based on the Lagrangian approach. In our previous study, it was found that the method can reproduce the icing process of the super-cooled water droplets impinging on the NACA0012 airfoil and its complicated ice shape. For accurate simulations, heat transfer was considered among computational particles, which was not simulated in the previous studies. The simulation provided the feather-shaped ice reasonably. Furthermore, in order to evaluate the aerodynamic performance of the iced airfoil, the flow field around the iced airfoil is computed by the Eulerian approach. The ice shape obtained by the explicit-moving particles method is projected onto the computational mesh of the flow simulation. The results show that flow separation around the leading edge is promoted due to the ice shape and it results in the large increase of the drag coefficient. Due to the icing, the drag coefficient increases by about 100% for 120 seconds of the icing time.