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.