Hypersonic finite-rate chemically reacting viscous flows over an ablating carbon surface

Hypersonic finite-rate chemically reacting viscous flows over an ablating carbon surface have been analyzed using the viscous shock-layer method. The equilibrium catalytic wall condition was used to obtain the species concentration at the wall. Wall temperature distribution and mass-transfer rates were calculated from a correlation of experimental and theoretical results for the blowing parameter and the heat-transfer coefficient. The results for nonequilibrium air-injection and the ablating carbon surface mass transfer were compared. Of all the test cases considered, the ablating carbon case shows a 10 percent higher stagnation heat-transfer rate than the equivalent nonequilibrium air injection case. The effects of fully catalytic, noncatalytic, and equilibrium catalytic wall boundary conditions were also compared.