飞机尾涡流场参数的仿真计算方法研究综述  

Review on the artificial calculating methods for aircraft wake vortex flow field parameters

作　　者：魏志强[1] 屈秋林[2] 刘薇[1] 徐肖豪[1] WEI Zhiqiang;QU Qiulin;LIU Wei;XU Xiaohao(College of Air Traffic Management,Civil Aviation University of China,Tianjin 300300,China;School of Aeronautic and Engineering,Beihang University,Beijing 100028,China)

机构地区：[1]中国民航大学空中交通管理学院,天津300300 [2]北京航空航天大学航空科学与工程学院,北京100028

出　　处：《空气动力学学报》2019年第1期33-42,共10页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(U1533116;U1633125);中国民航大学中央高校基本科研基金(3122017067)

摘　　要：作为缩减尾流间隔、提高运行效率的研究基础,尾涡流场的仿真计算技术是国内外民航空管研究领域的一个研究热点。在飞机尾涡流场的数值模拟方面,介绍了雷诺平均、大涡模拟和分离涡模拟方法在流场数值模拟方面的研究现状及存在问题;在尾涡流场参数的快速仿真计算方面,综述了典型计算模型的特点及存在的主要问题,包括CROW不稳定性、Greene消散模型、APA消散模型、TDAWP消散模型、D2P消散模型和三阶段消散模型等,分析了上述模型的精度与应用情况。最后对国内外研究现状进行了总结分析,提出了该领域未来的研究方向。As the basis of the research on reducing wake vortex separations, numerical simulation and constructing of fast-models for simulating wake vortex have become the focus of many international ATM research institutes. In the research field of wake vortex numerical simulation, the formation, evaluation and decay of wake vortex are calculated based on RANS, LES or DES methods. These data can help to reveal the regulation of wake vortex, and can provide basic foundation for constructing wake vortex models. In the field of fast simulation of wake vortex, Some organizations have done many theoretical researches on the formation and dissipation of wake vortex, attempting to deduce the behavioural characteristics of wake vortex by establishing complex mathematical models, including CROW instability, Greene model, APA model, TDAWP model, D2P model and the three-phase decay model, etc. The research status quo is analyzed and the key works in the next phase are also provided.

关 键 词：尾流间隔 尾涡流场 数值模拟 消散模型 地面效应 

分 类 号：V212.133[航空宇航科学与技术—航空宇航推进理论与工程]