侧风影响下航空器尾涡LES数值模拟

为保障航空器运行安全、提高飞行效率，用ICEM CFD 和Fluent软件采用大涡模拟（LES）方法对不同侧风下航空器进场尾涡进行数值模拟，研究进近阶段侧风对尾涡的影响。本文阐述了大涡模拟的原理，构建了空客A330-200机翼的构型和高网格质量的计算域，并模拟仿真飞机在无侧风条件下和侧风分别为3、5 、7 m/s的尾涡，量化分析侧风对尾涡演化规律和扩散趋势的影响。结果表明，侧风越大，尾涡的耗散速度越快 ，并且侧风对下风涡的影响大于上风涡。

Numerical Simulation of Aircraft Wake Vortex LES Under Crosswind Effect

In order to ensure the safety of aircraft operation and improve flight efficiency, ICEM CFD and Fluent software were used to conduct numerical simulation of aircraft approach wake vortex under different crosswind conditions by using large Eddy simulation (LES) method, and the influence of crosswind on the wake vortex during approach stage was studied. In this paper, the principle of large eddy simulation (LES) is described, and the computational domain of the configuration and high grid quality of the wings of Airbus A330-200 is constructed. The tail vortexes with no crosswail and with positive crosswail of 3m/s, 5m/s and 7m/s are simulated, and the influence of crosswail on the evolution and diffusion trend of the tail vortexes is quantitatively analyzed. The results show that the larger the crosswire is, the faster the dissipation speed of the trailing vortex is, and the influence of the crosswire on the leeward vortex is greater than that on the windward vortex.