Numerical simulation and analysis of flow patterns near a reentry space vehicle with firing rocket engines in the vicinity of the landing surface

The results of the numerical simulation of jets interaction of landing multi-nozzles engine with landing field are presented for recovery capsule of segment-conical form. The diffluent jets flow on landing surface and induced by jets flow near capsule are calculated. The investigations were carried out for several distances between landing surface and capsule. For each case the steady-state was achived. The time for realization steady-state flow and the values of the aerodynamic forces induced by ambient gas fluxes were defined. It was obtained that these values dependence from landing surface distance has monotonic character. In the configuration of engine nozzles under consideration the depression occur on all surfaces of the capsule. The force that deboost the engine thrust in vertical direction has place. In this case the gas flux that directed to capsule front part is formed. The calculations at deviations of the longitudinal capsule axis were realized. The flow structure and the effect on the aerodynamic characteristics were studied. The investigation of the engine thrust decreasing on parameters under consideration was actualized. In this case the engine thrust decreasing was modeling by jets pressure degression as well as the jets cross-section reduction. The visualization of spatial unsteady vortex structure is implemented. The numerical simulation is 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.