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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.
A two-dimensional low magnetic Reynolds number MHD (electromagnetic fluid dynamics) equation was established to introduce the electromagnetic source term, and the viscous flow field of two-dimensional hypersonic two-dimensional precursor / inlet was numerically simulated. The effect of MHD control on the viscous effect of inlet was further analyzed based on the basic characteristics of the viscous flow field in the design Mach number under non-designed conditions. The results show that the MHD control can effectively restrain the non-design conditions The inner surface of the inlet separation of the surface layer to improve the thermal condition of the upper wall to balance the heat load between the upper and lower wall; viscous effect, inlet flow field and performance parameters with the magnetic induction intensity of the law and The results of the non-viscous model are quite different. The influence of viscosity on the magneto-fluid-controlled hypersonic inlet can not be neglected.