不同侧风类型影响下的飞机尾涡数值模拟研究

在航空飞行中，低空风切变极易对处在起飞爬升或进近着陆阶段的飞机带来安全隐患，严重时会导致飞机失速甚至坠毁。低空风切变往往还具有持续时间短、尺度小、突发性强等特点。因此在中国民航和通用航空业高速发展的背景下，加强对飞机遭遇低空风切变的数值模拟仿真和研究具有重要意义和实际价值。采用SST模型并使用FLUENT计算尾涡演化，通过构建H-B尾涡耗散二维模型，应用ANSYS FLUENT UDF(user defined function)编译环境侧风不同的7种情况进行尾涡耗散机理的数值模拟，通过对比成都双流机场实地探测的尾涡发现在非线性垂直切变影响下侧风和涡诱导速度的叠加会导致尾涡对周围的压力分布不对称，引起尾涡对倾斜。

Numerical simulation of aircraft wake vortex under the influence of different crosswind types

It is very likely to bring safety hazards to the aircraft in the takeoff and climb or approach and landing phase for low-level wind shear in aviation flight. In severe cases, it can lead to aircraft stall or even crash. Low-altitude wind shear often also has a short duration, small scale, sudden and strong characteristics. Therefore, it is of great significance and practical value to strengthen the numerical simulation and research on aircraft encountering low-altitude wind shear in the context of the rapid development of China''s civil aviation and general aviation industry. The SST model and FLUENT were used to calculate the wake vortex evolution. ANSYS FLUENT UDF (User Defined Function) was applied to compile seven cases with different environmental side winds for numerical simulation of the wake vortex dissipation mechanism by constructing a two-dimensional model of H-B wake vortex dissipation. It is found that the superposition of side wind and vortex-induced velocity under the influence of nonlinear vertical shear will lead to asymmetric pressure distribution around the vortex, causing the vortex pair to tilt by comparing the vortex detected in the field at Chengdu Shuangliu Airport.