Validation of a Multiscale Approach in Problems of Supersonic Flow Around Blunt Bodies

The problem of modeling gas flows near high-speed flying vehicles and descent spacecraft is currently highly relevant. The requirements for the quality of this type of research have increased significantly. One way to improve modeling results is to use multiscale approaches. This work suggests a multiscale parallel computing technology based on a combination of continuum mechanics and molecular dynamics models, using grid and non-grid calculation algorithms. We demonstrate and validate the suggested technology by considering the solution of a problem about a flow around the surface of a high-speed vehicle. In this case, we take into account the processes of heat and mass transfer in both the boundary gas layer and the near-surface layer of the vehicle’s outer solid shell. The main focus is on the formulation of macroscopic boundary conditions and the parallel implementation of a multiscale approach. To test this approach, we computed the flow near a blunt-shaped spacecraft descending through the Earth’s atmosphere. The computation results show the performance of the proposed computing technology and the efficiency of the parallel program based on it.