Numerical Simulation of Finite Catalysis Model at the Balanced Radiation Wall

In this paper, the numerical method of finite catalysis at the balanced radiation wall of the hypersonic vehicle was developed. The numerical simulation results were compared with the wind tunnel experimental data of the re-entry capsule, and the influence of finite catalysis under balanced radiation wall on the aerodynamic thermal environment was further studied for a typical hypersonic vehicle with a blunt bi-cone. Numerical experiments on the shape of the re-entry capsule show that the heat fluxes under the boundary conditions of full catalysis and non-catalysis deviate greatly from the wind tunnel test results, and the heat flux obtained using the finite catalysis model is in good agreement with the wind tunnel test results. Studies on a typical hypersonic vehicle with a blunt bi-cone show that under the balanced radiation wall, the catalytic recombination coefficient of oxygen atoms near the stagnation point is about 0.17, that of nitrogen atoms is about 0.026, and that in the large area is reduced to 0.005 3 and 0.01, respectively. In terms of the heat flux at the stagnation point, the peak heat flux of the full catalyzed wall is about 21% higher than that of the finite catalysis, and the peak heat flux of the non-catalyzed wall is about 29% lower than that of the finite catalysis.