Viscosity effect of hypersonic inlet based on magnetohydrodynamic control

Two-dimensional steady-state flow equations coupled with low Reynolds number MHD(magnetohydrodynamic) effects were solved with MHD equations to study the viscosity effects of a MHD controlled hypersonic forebody/inlet. The numerical results showed some typical characteristics of viscous flowfield at the inlet when flight Mach number was larger than the designed value. Furthermore, the viscosity effect of inlet with MHD interaction was taken into discussion. The result analysis indicates that shock-induced boundary layer separation at the inlet can be restrained, and the maximum temperature near the interface of the inlet can be significantly lowered by implementing MHD control. Additionally, it is particularly true that the flow and performance parameters of MHD controlled inlet profiles versus magnitude force of the magnetic are fairly different when the viscosity is taken into consideration.