飞机机翼液滴撞击特性数值仿真

Numerical Simulation of the Impingement Characteristics of Droplets on Aircraft Wings

飞机在结冰气象条件下飞行时,大气中的液态水在部件表面冻结并累积成冰,是导致飞行事故的主要隐患。本文采用有限体积法求解了低速粘流的时均N-S方程,获得空气流场分布及各种流场特性。对NACA0015翼型前缘结冰进行了系统的研究给出了机翼表面水滴撞击特性的计算方案和步骤,计算得到了单尺寸、多尺寸分布水滴在翼面的局部收集系数及液滴的运动轨迹。结果表明,考虑水滴直径的多分散性后,机翼前缘的撞击极限发生变化,收集系数的最大值也高于单分散性。

The major hazard for the flight safety is the freezing and accumulation of ice of liquid water in the atmosphere on the surface of the parts of an aircraft flying under icing meteorological conditions. In this paper,the N-S equation of the lowviscous flowis solved with finite volume method to derive the distribution and characteristics of the air flowfield. This paper,on the basis of the systematic analysis of the ice shape of the front of NACA0015 airfoil,provides the calculation scheme and procedure of the trajectories of the water droplets on the surface of the wings and calculates the local collection coefficiencies of the single/multi-dispersed droplets distribution on the airfoil and the trajectory of droplets. The results showthat it renders a more accurate calculation of the ballistic limit and a larger maximum of the collection coefficiency taking the poly-dispersity of the diameters of water droplets into consideration.