Influence of the temperature of the surface of an axisymmetrical body and forward radiation on the distribution of a radiant flux on its surface in hypersonic flow-past

Abstract

A solution is obtained of the flow-past problem for an axisymmetrical body with steady-state hypersonic nonviscous, space-radiating gas flow in a hypersonic approximation. It is shown as illustrated by the example of flow-past of a sphere by an air flow, that the relative distribution of the radiant flux weakly depends on a calculation of surface re-radiation, while the size of the radiant flux substantially depends on body temperature TW at a critical point. The distributions of radiant flux for sphere flow-past by a CO2-N2 gas mixture (at TW = 0) are calculated using a previously developed method. It is shown that different CO2 contents in the initial mixture of the incident gas flow weakly affect this distribution. The dependence of the distribution of the radiant flux and departure of the shock wave on the boundary condition for gas enthalpy in the pressure shock, taking into account forward radiation, is investigated. Asymptotic expressions are obtained for sphere flow-past for the case of a strongly radiating gas. Distributions of the radiant flux for different assumptions for the boundary conditions in shocks are calculated.