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Numerical investigation for effect of heating area on ice accretion in NACA012 airfoil

DOI: 10.1615/THMT-18.560
pages 553-556

S. Uranai
Graduate School of Mechanical Engineering, Tokyo University of Science, 6-3-1 Niijuku, Katsushika-ku, Tokyo, 125-8585, Japan

Hiroya Mamori
Department of Mechanical Engineering, Keio University, Hiyoshi 3-14-1, Kohoku-ku, Yokohama 223-8522,Japan; Department of Mechanical Systems Engineering Tokyo University of Agriculture and Technology 2-24-16 Koganei City Naka Town Tokyo; Tokyo University of Science,6-3-1 Niijuku, Katsushika-ku, Tokyo, 125-8585, Japan

Naoya Fukushima
Department of Mechanical and Aerospace Engineering, Tokyo Institute of Technology, 2-12-1 Ookayama, Meguro-ku, Tokyo 152-8550, Japan; Frontier Research Center for Energy and Resources, The University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo, Japan; Department of Prime Mover Engineering, Tokai University, 4-1-1, Kitakaname, Hiratsuka-shi, Kanagawa, Japan

Makoto Yamamoto
Department of Mechanical Engineering, Tokyo University of Science, 6-3-1 Niijuku, Katsushika-ku, Tokyo, 125-8585, Japan

Abstrakt

Ice accretion is a phenomenon that super-cooled water droplets impinge and accrete on wall surfaces. For aircraft, icing phenomenon decreases the aerodynamics performance or induces serious accidents. Some devices have been developed for de- and anti-icing. Recently, an electro-thermal heater is often adopted as de- and anti-icing system for wings due to its simplicity, although the disadvantage is to require large power consumption of airplane. Therefore, an optimization of the power supply and the location of the electro-thermal heater are needed. In the present study, we conducted icing simulations of a NACA0012 airfoil with an electro-thermal heater on the leading-edge surface. Effects of the heating area on the icing phenomena are numerically investigated. To perform the simulation, we improved the Extended Messinger model which is widely used in the thermodynamic computation of icing simulations. The icing simulations are performed for different heater areas and we compare the ice shapes and the drags of the airfoils.

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