侧风条件下的翼尖涡数值模拟研究

Numerical simulation study of wingtip vortices under crosswind conditions

现有的通过数值模拟方法对飞机尾流进行的研究,多是基于矩形机翼半模对称得到全局流场,因此无法模拟侧风条件下的尾流流场结构。通过对典型中型机A330_200飞机构建全机模型并进行网格划分,针对进近阶段选择典型迎角,使用添加旋转修正的SST-RC模型模拟全机尾流场结构,分别计算无侧风、2 m/s、5 m/s典型侧风下的流场结构。实验结果表明,由于侧风的存在,飞机尾流的四涡系结构会向侧风下游产生偏移。2 m/s代表的较小侧风条件可以加速四涡系结构的耗散,有利于缩减尾流间隔。但侧风速度对尾涡的耗散作用并不成正比;5 m/s代表的较大侧风条件下,由于能量输送,会使侧风下游翼尖涡与侧风上游翼根涡两束涡系涡量提升约68%,但由于较大侧风可以更快将尾涡吹离航道,因此侧风整体上有利于翼尖涡的耗散。

A model of a typical mid-size A330_200 aircraft was constructed and meshed,a typical angle of attack was selected for the approach phase,and the SST-RC model with rotation correction was used to simulate the structure of the wake field of the entire aircraft.Experimental results show that due to the existence of crosswinds,the four-vortex structure of the aircraft wake will shift to the downstream of the crosswind.The crosswind speed is not proportional to the dissipation of the wake vortex;under the condition of a large crosswind represented by 5 m/s,due to energy transmission,there will be two vortices in the downstream wing tip vortex of the crosswind and the wing root vortex in the upstream of the crosswind.The vorticity was increased by about 68%,but because the larger crosswind can blow the wake vortex away from the channel faster,the crosswind was conducive to the dissipation of the wingtip vortex as a whole.