To investigate the flow control effects of applied magnetic fields on hypersonic vehicles, four magnetic field configurations—stagnation-point dipole, globally uniform, dual-window locally uniform, and parameterized fields—were comparatively studied for the OREX reentry condition (Ma=9.06, H=48.4km). A 10-fold scale-up model was employed to achieve a turbulent Reynolds number of Re=2.23×106. The thermochemical nonequilibrium Navier-Stokes equations were solved using a two-temperature model, an 11-species chemical reaction mechanism, and the k-ω SST turbulence model. Results show that the parameterized magnetic field achieved optimal flow control performance, with the total wall heat flux reduced by 8%~14%. In the shoulder region, ionization reactions were significantly enhanced by the parameterized field, resulting in an approximately 67% increase in electron number density. A unique vibrational temperature overshoot phenomenon (Tv > T) was observed along the stagnation line under the dipole field configuration. Wall heat flux decomposition analysis indicated that vibrational heat flux accounted for over 99% of the total, demonstrating the necessity of the two-temperature model. These findings provide a theoretical foundation for magnetic field optimization design in magnetohydrodynamic thermal protection technology.