Analytical study of thermodynamics and heat transfer of high-temperature and high-velocity flow field behind shock waves is an important problem involving the design and heat transfer analysis of vehicle thermal protection system (TPS).The flow fields of the Apollo AS-202 return capsule aviating in the earth atmosphere of six cases (the Mach number varying from 15.52 to 22.63) and the Huygens vehicle aviating in the Titan atmosphere of six cases (the Mach number varying from 17.29 to 24.47) were simulated by using conservation integral form of Navier-Stokes equations with multi-species

nonequilibrium molecular thermal excitation and chemical reactions

based on the high-resolution total variation diminishing (TVD) scheme.Thermodynamics and heat transfer of high-temperature and high-velocity flow field behind bow shock were studied

and the wall heat flux density

wall temperature and Stanton number were in good agreement with the flight data.These results are useful for design of correlative vehicles'TPS.