Three-dimensional Navier-Stokes equations in high temperature real gas model and perfect gas model are solved for hypersonic entry process. Good agreement is achieved between numerical results, reference values and flight data of Viking, which validates physical-chemical models and numerical methods. Aerodynamic prediction of Mars Pathfinder proves that results of real gas model are close to LAURA. Perfect gas model with effective specific heat ratio is capable of computing lift and drag coefficients. At 2° angle of attack, MPF exhibits static instability along trajectory, which perfect gas model failed to catch on. It is considered that main reasons of static instability are sonic line shifting around shoulder in windward, subsonic area varying and subsonic bubble occurring in leeward. They result in different pressure change in shock layer and in transportation process from expansion zone to upstream.

Numerical analysis is made to study thermodynamic models for surface thermal environment of Mars entering vehicles. It shows that flow in stagnation region stays almost in thermal equilibrium. As flight altitude rises,flow changes to thermal nonequilibrium. Heat transfer rate keeps the same in different thermodynamics models,if non-catalytic condition is set on the wall. In simulations with full-catalytic wall conditions,heat transfer rate in thermal non-equilibrium model become higher,due to difference of characteristic temperature in chemical reactions. The stronger the effect of thermal non-equilibrium is,the greater the characteristic temperature change and the heat transfer rate will be.

Hypersonic flows around a blunt body are studied with numerical simulation and theoretical analysis.Correlations between plasma prediction and gas components are obtained.It shows that it is Mach number which affects the peak number density of electrons.Numerical simulation agrees with theoretical analysis well.Differences between two gas models get greater as Mach number increases.The differences follow same trend at back taper with stagnation region.A 11-species chemical model should be applied to increase accuracy when reentry capsule flight at height of 60 km and Mach number is over 23.

Three-dimensional Navier-Stokes equations in real gas models are solved with a parallel code to analyze aerodynamic characteristics of Mars Science Laboratory in hypersonic entry in Martian atmosphere. Good agreement between numerical results and flight data of Viking validates physical-chemical models and numerical methods. It shows that impacted by real gas effect,shock layer thickness is reduced; drag coefficient rises,lift coefficient is almost unchanged. Difference of trim angle between real gas and perfect gas is about 2.2°; As keeping altitude,greater Mach number results in greater drag and pitching moment coefficient. Difference of trim angle varies from 1.6° to 2.6°. Increasing Mach number enhances real gas effect. As keeping Mach number,increasing altitude weakens chemical reactions behind the shock,but it has weak influence on aerodynamic coefficient.