Method of Design of Supersonic Flow about Sphere Based on AUSM Finite-Difference Scheme

A method of the numerical simulation of a flow about a sphere by a supersonic perfect gas flow is set forth. The method is based on dividing an equation system of viscous heat-conducting gas in two equation groups: one of which consists of Navier-Stokes equations and is integrated using AUSM finite-difference scheme, the other group includes the energy conservation equation and is integrated using an implicit method of integration of a five-point finite-difference scheme. Results of numerical studies of the flow about a sphere in the whole flow area from a bow shock wave to a far wake are given for the incident flow conditions corresponding to a certain point of one of possible trajectories of a spacecraft entering the atmosphere. A relation is shown between numerical solutions and applied finite-difference grids. Recommendations are given on construction of optimal grids.