Heterogeneous catalysis plays an important role in causing the aerodynamic heating surge in the hypersonic nonequilibrium flow/thermal protection material interactions for high-speed aircrafts. To model the flow/material interaction problem, a gas-interface-solid coupling method for heterogeneous catalysis was established by introducing interface balance relation into the coupling framework of nonequilibrium Navier-Stokes equations and thermal conduction equation. The influence of coating heterogeneous catalysis on heat transfer into the heat shield of a blunt body was then numerically investigated to reveal the catalysis-induced aerothermodynamics. The coupling simulation results reveal that the codominant role of material mediated catalysis and gaseous reactions on boundary layer and their induced near-wall evolutions are the main features of the chemically reacting boundary layer that differ from the conventional boundary layer theory. It was found that catalytically inert coatings can weaken the local aerodynamic heating due to the low activity of local catalysis and enhance the downstream catalytic heating through driving atomic species to the downstream region. Appropriate layouts of thermal protection coatings can make full use of the nature of catalytic exothermicity to effectively manage hypersonic flow and catalysis-induced heat-transfer characteristics for the lightweight and low-redundancy thermal protection designs of future spacecraft.
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