Numerical simulation of some problems of recovery capsule aerodynamics

The numerical simulation results of the flow near the recovery capsule with detaching frontal heat shield and jets interaction of the landing multi-nozzles engine with landing field are presented for segment-conical form capsule. The flow structure and the aerodynamic characteristics are studied. The visualization of spatial unsteady vortex structure is implemented. The calculations are based on the unsteady finite-difference schemes of the flux method, approximating the conservation laws in integral form. The numerical simulation is carried out on parallel algorithms and realized on cluster multiprocessor systems.