LAUSR

The influence of magnetohydrodynamic flow control on radiative heating in Mars entry flight is examined using a one-way coupling numerical approach of magnetohydrodynamics and radiative heat transfer where a steady solution of computational magnetohydrodynamics is employed as the input data of radiative heat transfer calculation. A sphere-cone test body with a sphere radius of 0.875 m is assumed to have a velocity of 7.9 km/s at an altitude of 50 km; an onboard magnet is assumed to generate a strength of 0.3 T at the stagnation point. Numerical results show that magnetohydrodynamic flow control expands a shock layer, enlarging a high-temperature layer involving strong emission and absorption ahead of the test body. Consequently, the radiation intensity arriving at the wall around the stagnation point is decreased by magnetohydrodynamic flow control because of the more substantial effect of the intensification of absorption than that of emission. In contrast, the radiation intensity arriving at the wall far from the stagnation point is increased by it because of the more substantial effect of the intensification of emission. Thus, the influence of magnetohydrodynamic flow control on the radiative heating in Mars entry flight strongly depends on the position on the wall.