Abstract
Radiative aerothermodynamics of large-scale space vehicles, similar to Orion International Space Station Crew Exploration Vehicle (ISS CEV), is investigated for Earth orbital entry at two angles of attack. Brief description of used two- (2D) and three- (3D) dimensional radiation gasdynamic models of physically and chemically nonequilibrium, viscous, heat conductive and radiative gas of complex chemical composition is presented. Two-dimensional calculations in view of radiation gas dynamic interaction for axysimmetric flow have been performed. It is shown that the use different models of non-equilibrium dissociation result in significant differences in temperature distributions in shock layer, as well as in the radiative heating of streamlined surface. Results of comparison of convective and radiative heating of ISS CEV at two angles of attack (α = 0 and 25 0 ) are presented.
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