Modeling of chemical and thermodynamical nonequilibrium flows about the bodies entering over plane trajectories

The approach and results of a numerical study using the model of interaction between vibration and dissociation are presented for the hypersonic flow about the blunt bodies. Calculations with variable nose radii for two border plane trajectories, bounded possible launching, and for the trajectory of “Buran” orbital vehicle are performed. It is concluded that the influence of thermodynamic nonequilibrium on heat fluxes is significant for practically all thermal tension parts of trajectories.