通过求解薄层近似的Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程，数值模拟了带座舱飞船高超声速粘性绕流，首次系统地给出了攻角为５°、１０°、２０°、３０°和４０°情况下的物面分离形态、横截面流线形态、纵剖面流线形态以及旋涡沿涡轴的演变形态。分析和比较表明，本文采用数值可视化方法给出的流场拓扑结构与相应的拓扑规律完全吻合。在飞船后体流场横截面流线中，本文发现了稳定的极限环流态，该极限环涡心处沿涡轴方向的速度是超声速的，且速度梯度（　）０＞０，这与低速流情况是相反的，本文得到的这一结果证实了相应的理论结论。 By solving the Navier-Stokes equations approximating to the thin layer, the hypersonic viscous flow around the cabin with the cabin was numerically simulated. For the first time, the objects with the attack angles of 5 °, 10 °, 20 °, 30 ° and 40 ° Surface morphology, cross-sectional streamlines, longitudinal streamlines, and evolution of vortices along the vortex axis. Analysis and comparison show that the topology of flow field given by numerical visualization method is in good agreement with the corresponding topological law. In the cross-sectional flow line of the body flow field behind the spacecraft, the steady-state limit-state circulation is found. The velocity of the vortex in the direction of the vortex axis is supersonic and the velocity gradient () 0> 0, The opposite is true, and the result obtained in this paper confirms the corresponding theoretical conclusion.