翼型积冰的数值模拟

Numerically simulating of ice accretion on airfoil

本文采用计算流体力学的方法对NACA0012翼型前沿的Rimeice积冰进行了预测。在流场计算中,用有限体积(FV)法对二维定常不可压粘流的时均N-S方程进行离散求解;采用四阶龙戈-库塔(RK)法求解水滴运动方程;假定水滴在与翼型相碰撞的点处完全凝结,并且冰沿着与当地翼型表面法向一致的方向增长,以此来预测积冰的形状。文中同时对迎角为4°时结冰翼型的气动特性进行了分析。

Rime ice accretion on the leading edge of the NACA 0012 airfoil is predicted using CFD method .The flow field is calculated by solving the 2D steady incompressible NS equations with finite volume method. A 4order Runge Kutta method is used to solve the droplet trajectory equation. Ice shape is determinated with the assumption that all droplets freeze at their points of impact and that the ice grows in the direction normal to the surface. The method yields ice shapes that are in good agreement with the results found in the literature. The comparison among the results shows that viscous effects can affect ice shape. Aerodynamic characteristics of the iced airfoil for 4° angle of attack are also analyzed in the paper. 