ARJ21飞机尾涡在侧风条件下的近地演化数值模拟  

Numerical simulation on near-field evolution of wake vortices of ARJ21 plane with crosswind

作　　者：张钧铎 左青海 林孟达 黄伟希[1] 潘卫军[2] 崔桂香[1] ZHANG Junduo;ZUO Qinghai;LIN Mengda;HUANG Weixi;PAN Weijun;CUI Guixiang(School of Aerospace Engineering,Tsinghua University,Beijing 100084,China;Civil Aviation Flight University of China,Guanghan 618307,China)

机构地区：[1]清华大学航天航空学院,北京100084 [2]中国民用航空飞行学院,广汉618307

出　　处：《航空学报》2022年第5期155-167,共13页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金民航联合基金(U1733203);民航安全能力建设项目(TM 2019-16-1/3)。

摘　　要：尾流间隔是飞机起降安全的重要保障,也是制约机场效率的重要因素之一,而飞机尾涡的近地演化特性与规律是制定尾流间隔系统的基础和依据。因此,研究国产机型的尾涡近地演化特性与规律具有重要的现实意义。应用升力面模型初始化尾涡流场,采用自适应网格大涡模拟技术数值研究ARJ21客机尾涡在侧风条件下的近地演化过程,并分析在不同侧风条件下尾涡的演化与衰减特性。数值结果显示上游涡与下游涡演化具有不对称性,其中下游涡衰减更快,但移动距离更远,并且侧风越强尾涡衰减越快。此外,根据ARJ21尾涡的数值结果分析了不同机型跟随ARJ21进近时的安全性,发现重型机可不考虑其尾涡影响,而中型机和轻型机需根据气象条件选择合适的最小尾流间隔。Wake separation is crucial to the security of aircraft landing,and is also an important factor of improving airport efficiency.The characteristics of near-field evolution of wake vortices is the foundation of the design of wake separation system.Therefore,it is of great practical significance to investigate the near-field evolution of wake vortices of domestic aircraft.In the present study,the effect of crosswind on the near-field evolution of wake vortices of ARJ21 plane,initialized by the lift-drag model,is analyzed by using the large eddy simulation based on adaptive mesh.The numerical results show that the evolution of the upstream vortex and downstream vortex is asymmetric.The downstream vortex decays more rapidly and translates farther than the upstream vortex,and the wake vortices decay more rapidly as the cross-wind gets stronger.In addition,the security of the following plane after ARJ21 is also analyzed based on the numerical results of the ARJ21 plane.It is found that the heavy plane is not affected by the wake vortices of ARJ21,whereas the medium-sized and light planes require adequate wake separation according to the weather condition.

关 键 词：ARJ21飞机 尾涡 近地演化 侧风 大涡模拟 自适应网格 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]