Numerical research of gas models on the aerodynamic characteristics in electronic transpiration cooling coupling magnetohydrodynamics

Hypersonic flows feature low density, high velocity, and strong thermochemical nonequilibrium, leading to severe aerodynamic heating. To address this challenge, this study develops a coupled thermal protection method [electronic transpiration cooling coupling magnetohydrodynamic, (METC)], by integrating magnetohydrodynamic equations and electron transpiration cooling boundary conditions into the thermochemical nonequilibrium Navier–Stokes framework. The influences of different electrical conductivity and chemical reaction kinetics models on the flow field and aerothermal characteristics are systematically evaluated. The shock standoff distance decreases progressively from the Raizer, Otus, and Nagata models to the Chapman–Cowling model. The Raizer model predicts the lowest wall and shock-layer temperatures, reducing stagnation temperature by up to 11.4%, while the Chapman–Cowling model yields the highest wall heat flux. All gas models consistently identify the blunt nose as the region of peak qETC and qRad. Significant variations in the Lorentz force arise from different electrical conductivity models due to distinct ionization levels, whereas chemical kinetics models show comparatively minor effects. Temperature differences at the blunt nose remain below 1.4%, and stagnation point heat flux variations within 11.6%. These results highlight the critical impact of the electrical conductivity model on METC performance and the relatively limited sensitivity to the chemical reaction kinetics model.