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基于非结构网格对翼型表面的积冰进行了数值模拟研究.通过求解气体欧拉方程得到翼型的绕流流场,使用穿透型壁面边界模拟水滴对翼型表面的撞击,采用迭代法对水滴控制方程进行数值求解,得到翼型表面的水滴收集特性;采用不同的积冰冻结模型模拟霜冰和明冰的冻结过程;利用冰层时间推进法模拟积冰过程,基于积冰法向生长假设生成积冰外形.对NACA 0012翼型霜冰和明冰的结冰情况进行了预测研究,通过将冰形预测结果与实验结果进行对比说明所提出的积冰模拟方法是有效的,最后分析了积冰对翼型气动特性的影响.
Based on unstructured grid, the ice accretion on the airfoil surface was numerically simulated, and the flow field around the airfoil was obtained by solving the Euler equation of the gas. The penetrating wall boundary was used to simulate the impact of the water drop on the airfoil surface. Method was used to solve the water droplet governing equations numerically to obtain the characteristics of water droplets collected on the airfoil surface. Different ice-freezing models were used to simulate the freezing process of frost and clear ice. The ice- The ice accretion is generated to the growth assumptions.A prediction study on the icing conditions of NACA 0012 airfoil frost and clear ice is made. It is shown that the proposed ice flooding simulation method is effective by comparing the ice pre-ice prediction results with the experimental results, Finally, the effect of ice accretion on aerodynamic characteristics of airfoils is analyzed.