Numerical Simulation of Flow Field at Descent Vehicle Entry into Earth’s Atmosphere

Results are given of numerical simulation of the ideal gas supersonic flow about the descent vehicle Fire II at its entry into the Earth's atmosphere. The simulation has been based on the numerical solution of Navier-Stokes equations system on non-structured grids in 3D problem statement with allowance for gas compressibility.Peculiarities of flow field structure and thermal physics processes in the whole disturbed area around the descent vehicle from the bow shock wave to the far trail, behavior of local aerodynamic and thermal characteristics, and also structures of the complex 3D vortex-type flows near the surface under conditions of the undisturbed incident flow which correspond to various points of possible paths of the descent vehicle entry into the atmosphere are investigated by methods of computational aerodynamics. Calculations are performed in the range of angle-of-attack a from 0 to 20°.The influence of the angle-of attack a on the flow field, vortex near-surface flows, and local aerodynamic and thermal characteristics along the front (nose) and aft surfaces are studied within the framework of some models of turbulence. Results of calculations are compared to data of flight tests, laboratory experiments and data of the calculation and theoretical analysis given in the literature.