FEM-FCT is used to solve three-dimensional hypersonic inviscid flow.The flow fields around sphere,modified space shuttle orbiter and capsule type vehicle are gained on unstructured tetrahedron grids.The results show that the scheme is valid and has high resolution to shock waves.

The numerical solution of inviscid and viscous flow through convergent nozzles is presented from Euler equation and N-S equation. MacCormack explicit difference scheme is used with an improved artificial viscous term. The method employs the split of zone to overcome the instability near exit of the nozzeles. The results of a typical calculation are in good agreement with experimental data.

This paper deals with the finite element approximation of the axisymmetric Stokes flow on unbounded domains. In order to overcome the difficulties caused by the unbounded domains, the finite element method is combined with the classical analytical method and the equivalent boundary value problem on bounded domains is obtained, which is solved numerically by the finite element techneque. As an example, the Stokes flow around the sphere is calculated and the error estimate of the approximate solutions is given.