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.

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.

Three-dimensional algorithms solving laminar Navier-Stokes equations coupled with chemical reaction and transportation equations are developed.Detailed flow field and distribution of yield,dissociation and pumping rates and small signal gain are obtained which cannot easily be got in experiments.The reason that experimental results are not as good as that in theories is analyzed.Furthermore,a better way to operate the system is suggested.It is shown that the mixing and chemical process in a nozzle of limited length is not complete due to the high speed in supersonic mixing zone and low mixing efficiency.Higher iodine concentration for speeding up chemical reaction causes insufficient of singlet oxygen,so as an unreasonable gain.A primary flow without buffer gas is claimed necessary and essential to reduce flow velocity and assure mixing process and chemical reaction accomplished before arriving the cavity.With an appropriate flow rate ratio,a small signal gain can reach 1.3% cm^-1.

Three-dimensional CFD technology is applied in a RADICL model by solving laminar Navier-Stokes equations and transportation equations to study iodine molecule dissociation rate,iodine atom pumping rate,singlet oxygen yield rate and small signal gain at different flow rate ratio of primary and secondary flow.It is found that an appropriate flow rate ratio plays an important role in spatial distribution of the small signal gain.Rich or poor oxygen conditions go against with a proper gain.

Three-dimensional CFD technology is applied in an RADICL model by solving laminar Navier-Stokes equations and transportation equations. Mixing and reaction of flows, gas-dynamics fields and gains are studied at different jet intensity. It is found that the penetration depth plays an important role for special distribution of small signal gain macroscopically. Strong impinges between jets and unsteady structures are induced by over-penetration in mixing flow field.