輻射加熱を考慮したMHD Heat Shieldの数値シミュレーション

抄録

The MHD heat shield under the condition of the super-orbital reentry flight is numerically analyzed with consideration of the radiative wall heat flux. The flow field around a capsule body is computed by the two-dimensional computational magnetohydrodynamics code developed by the authors. The radiative wall heat flux is calculated by the structured package for the radiation analysis ``SPRADIAN''. The main results show that the convective wall heat flux decreases by applying the magnetic field, whereas the radiative wall heat flux increases. The increase in radiative wall heat flux by applying the magnetic field is mainly attributed to the expansion of the shock layer and the rise of the plasma temperature. Under a strong magnetic field condition, the total wall heat flux, which is defined as the sum of convective and radiative wall heat fluxes, increases by applying the magnetic field due to the increase in the radiative wall heat flux.