The fast and accurate simulation of aircraft wake vortices evolution and safety assessment of wake encounters are important in identifying the hazard zone of wake vortices, reducing wake separation, and increasing the capacity of airports. However, numerical simulation of wake vortices often takes a lot of time due to a large number of grids. In order to reduce the computation time, Solution-Based Dynamic adaptive mesh method is applied to compute the wake vortex evolution using FLUENT. Three cases with different ambient turbulence intensities are carried out with the large eddy simulation (LES) based on adaptive mesh. The numerical result shows that refiner meshes in the region of the vortex core generated by adaptive mesh method can more effectively capture the dynamics of vortices, identify more secondary vortices and reduce the numerical dissipation due to more compact vortex core resolution. Then, the rolling moment of the following aircraft is calculated and the hazard zone is identified for the aircraft pairing of A340 and A320. The results show that the safety of wake encounters has a close relationship with ambient turbulent intensity and development of vortex instability.

快速准确地模拟飞机尾流涡流演变以及对尾流相遇的安全性评估对于确定尾流涡流的危险区域，减少尾流分离和增加机场容量至关重要。然而，由于大量的网格，尾流涡旋的数值模拟通常会花费很多时间。为了减少计算时间，应用基于解决方案的动态自适应网格方法来利用FLUENT计算尾涡。通过基于自适应网格的大涡模拟（LES），对三种不同环境湍流强度的情况进行了研究。数值结果表明，采用自适应网格方法生成的涡旋核区域内的细化网格可以更有效地捕获涡旋动力学，由于更紧凑的涡旋核心分辨率，可以识别更多的次级涡旋并减少数值耗散。然后，计算后续飞机的侧倾力矩，并确定A340和A320飞机配对的危险区域。结果表明，尾流相遇的安全性与周围湍流强度和涡旋不稳定性的发展密切相关。