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所属单位：航空学院

发表刊物：IET Conf Publ

摘要：First of all, a numerical method is developed for automatic icing simulation on aircraft which consists grid generation, ice generation, grid upgrade after icing and solving The external flow field. The numerical method is validated through simulating the NACA0012 airfoil. Then, under the rime ice condition, the mechanism and regulation are studied where the angle of attack, flight velocity, diameter of water drops, chord length of airfoil and the thickness of airfoil are different Results show that the icing area slightly increases as the flight velocity increases with the same diameter of water drops. When the flight velocity is constant, larger diameter of water drops leads to a remarkable increase of icing area. Otherwise, a larger chord length and airfoil thickness of an airfoil results in smaller icing area respectively where the thickness of ice on stagnation point is smaller. © 2018 IET Conference Publications. All rights reserved.

是否译文：否

发表时间：2018-01-01

合写作者：Li, Longfei,王江峰,Xu, Cong

通讯作者：董昊