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采用杂交通量分裂的NND格式模拟了跨、超声速三角翼背风区的旋涡运动结构。结果表明，旋涡的截面结构依赖于涡轴上的速度与密度的乘积沿轴向的导数λ＝［（1／ρ）（ρu1／l）］，当它大于零时，涡心附近的截面流线向里转，而当它小于零时，涡心附近的截面流线向外转，λ由大于零变到小于零，涡心附近将出现一个稳定的极限环，多一次变号，将多出现一个极限环。对超声速的计算，λ出现了一次变号，横截面流态中出现了一个极限环，对跨声速的计算，λ发生两次变号，横截面流态中出现了两个极限环。对跨声速三角翼的计算得到了涡破裂现象并发现涡破裂是从螺旋型起始并逐步演变成泡型。在破裂区，流动具有弱非定常特性。数值结果验证了张涵信的拓扑分析结果。
The vortex motion structure in the leeward region of the transonic and supersonic wing was simulated by using NND format of hybrid flux splitting. The results show that the cross-sectional structure of the vortex relies on the axial derivative λ = [(1 / ρ) (ρu1 / l)] of the product of velocity and density on the vortex axis. When it is greater than zero, the cross- When it is less than zero, the cross-section streamline turns outwards near the vortex center, and λ changes from greater than zero to less than zero. A stable limit ring will appear near the vortex center, changing the sign more frequently A limit ring appears. For the calculation of supersonic velocity, a change of sign appears in λ, and a limit cycle appears in the cross-section flow regime. For the calculation of transonic velocity, λ changes twice and two limit cycles appear in the cross-section flow regime. The vortex rupture was calculated for the transonic delta wing and it was found that the vortex rupture started from the spiral and evolved into a bubble. In the rupture zone, the flow has weak unsteady characteristics. Numerical results verify the results of Zhang Han Xin’s topology analysis.