Surface chemical effects have great influence on the prediction of hypersonic nonequilibrium aerodynamic heating, and they are particularly complex in a dissociated carbon–oxygen environment for the possible use of Mars entry simulation. To clearly characterize the thermochemical behaviors and precisely predict the surface heat fluxes, a finite-rate surface chemical model involving the catalysis and ablation effects is developed, and the influences of catalysis, ablation, and their interaction on aerodynamic heating are parametrically discussed in detail. The computation finds that the surface thermochemical characteristics are dominated commonly by surface reactions and near-wall diffusion, depending on the balance of the levels of the chemical-reaction rate and the diffusional transport speed. The findings of this study indicate that both competition and enhancement exist between various surface reaction channels. They will compete for the species if they commonly consume the same reactant, whereas they will mutually enhance their heat fluxes if the product of one reaction channel supplies to the other. The surface chemical effects on aerodynamic heating can make assessments for the search and application of promising and profitable thermal protection materials based on the material catalytic and ablative characteristics in the scope of decreasing the weight of the thermal protection system.
Surface Chemical Effects on Hypersonic Nonequilibrium Aeroheating in Dissociated Carbon–Oxygen Mixture
Journal of Spacecraft and Rockets ; 55 , 3 ; 687-697
2018-02-13
11 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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