过冷水滴撞击结冰表面的数值模拟
Numerical Simulation of Supercooled Water Droplets Impingement on Icing Surfaces
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摘要: 为了计算过冷水滴撞击结冰表面,本文应用雷诺平均Navier-Stokes方程和k-ε两方程紊流模型计算结冰表面外的空气流场。用欧拉法建立了空气中过冷水滴的运动方程,并采用有限控制容积法对方程进行了数值计算。为了提高计算精度,方程中的对流—扩散项采用MUSCL格式进行了离散。计算结果表明过冷水滴的大小和机翼攻角的变化对结冰区的大小和水收集系数的影响很大。Abstract: It is well known that ice accretion on aircraft component would take place when an aircraft flies in clouds at sub freezing temperature.The presence of ice accretion on unprotected aircraft airfoil can change the airfoil shape and can lead to a number of aerodynamic degradation problems.To compute the supercooled water impingement on icing surfaces,the Reynolds averaged Navier Stokes equations and k ε model are used to simulate the airflow over the surface in the present paper.A Eulerian model for air flows containing water droplet is used to compute the water droplet trajectories.The finite control volume formulation is proposed to solve the droplet problem.In order to avoid the numerical diffusion and to increase the accuracy,the MUSCAL scheme is appropriated for approximating the convection terms of governing equations.The Navier Stokes equations are solved independently from the Eulerian droplet equations.While the velocity field of airflow is achieved,the droplet flow equations can be computed.Both the airflow and droplet equations are computed on non staggered meshes.When solving Navier Stokes equations,the pressure correction algorithm SIMPLER is adopted.Results show that changes in MVD and angle of attack have greater effects on impingement limits and collection efficiencies.
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Key words:
- aerospace propulsion /
- numerical simulation /
- anti-icing /
- de-icing /
- droplet trajectories
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