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飞机在飞行中形成的翼尖涡会使跟进的后机发生倾斜、滚转、失速等影响飞行安全的情况. 通过对尾涡机理的分析，本文建立了尾涡消散模型、运动模型，采用镜像涡方法，根据涡核间距加大的程度来评估地面效应影响的强弱，较好地反映地面效应对尾涡运动和消散的影响. 基于建立的模型，对尾涡流场进行仿真计算，计算结果与激光雷达实测或大涡模拟结果基本一致. 与常用的大涡模拟方法相比，文中计算模型具有形式简单、速度快的优点，可以用在机场尾涡间隔系统研究中.

Modeling and Simulating of Flow Field for Aircraft Wake Vortex

The wake vortex induced by the leading aircraft usually brings the dangerous state to the following aircraft such as incline, rolling, or stall. Based on the anglicizing of mechanism of wake vortex, the decaying and movement models are developed in this paper. In addition, using the methods of image vortex and considering the influence of ground effects, the paper determins the degree of influence by the increasing of space between the vortexes, which is suitable for anglicizing the influences of ground effects. With these models and methods, the filed of wake vortex is simulated and calculated, the results are similar to what calculated by the Large Eddy Simulation models and measured by the lidars. With the advantage of simple form, high speed, the proposed models can be used in the study of wake vortex safety spacing system of airport.