为了完善不同阶段、不同机翼构型下的飞机尾涡研究，深入揭示尾涡生成与演化的规律，针对爬升状态A330-200飞机尾涡进行仿真分析。首先，选取第2襟翼构型构建机翼模型；随后，进行非结构化网格划分；最后，设置1 500 m爬升高度的仿真环境，采用SST k-ω湍流模型进行数值模拟。通过涡量和Omega涡识别尾涡结构，进一步提取尾涡运动轨迹。并使用环量表征尾涡强度变化。结果表明，襟翼打开使翼尖涡初始强度降低95%，并诱导机翼生成了多涡对结构。随着涡系的不断融合，最终发展为稳定的四涡结构。演化初期翼尖涡间距不断减小；在8倍翼展处内襟翼涡下沉速率增加，内襟翼涡和翼尖涡的涡间距皆增大。内襟翼涡强度衰减速率高于翼尖涡，且更早进入快速衰减阶段。

To enhance understanding of aircraft wake vortex behavior across different flight phases and wing configurations, a numerical simulation analysis was performed for vortices generated by an A330-200 aircraft during the climb phase. A typical second-flap-configuration wing model was selected, and an unstructured mesh was constructed. The simulation environment was configured for a climb altitude of 1 500 meters, with numerical computations carried out using the SST k-ω turbulence model. Vortex structures were identified through combined vorticity analysis and the Omega vortex method, and corresponding trajectories were extracted. Circulation values were applied to characterize vortex intensity evolution. The results show that flap deployment reduces the initial wingtip vortex strength by 95% and induces the formation of multiple vortex pairs. Continuous merging processes within the vortex system lead to stabilization into a quadruple-vortex structure. During the early evolution stages, wingtip vortex spacing contracted. At eight wingspans downstream, an increased subsidence rate of the inner flap vortex is observed, together with expanded spacing between the inner flap vortices and the wingtip vortices. Inner flap vortices exhibite accelerated decay compared with wingtip vortices, entering the rapid dissipation phase earlier.