Abstract: 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.

Key words: Mars, thermodynamics model, aerothermal environment