基于磁流体控制的高超声速进气道黏性效应

Viscosity effect of hypersonic inlet based on magnetohydrodynamic control

建立引入电磁源项的二维低磁雷诺数磁流体动力学(MHD)方程组,对高超声速二维前体/进气道黏性流场进行了数值模拟.在给出了进气道高于设计马赫数的非设计工况下黏性流场的基本特征基础上,进一步分析了施加MHD控制对进气道黏性效应的影响.结果表明:施加MHD控制可以有效抑制非设计工况下内进气道表面的附面层分离,改善上壁面的热状况,平衡上、下壁面之间的热负担;黏性作用下,进气道流场及性能参数随磁感强度的变化规律与无黏模型计算结果存在较大差别,对磁流体控制的高超声速进气道研究不可忽略黏性的影响.

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.