A novel magnetohydrodynamic (MHD) flow control mechanism based on the magnetic induced vortex is proposed to improve the thermal protection performance and aerodynamic performance of reentry vehicles. The magnetic field based on the polygonal coil grid is designed to obtain different vortex forms. Five Lorentz force models are constructed to reveal the MHD interaction mechanisms of the magnetic induced vortex. By numerically solving the low-magneto-Reynolds-number equations, the flowfields of the two-dimensional cylinder and three-dimensional sphere with the different vortex forms are obtained. Two vortex forms are found in the side and head regions of the cylinder, respectively. Under the influence of the vortexes, the high heat flux, which may be higher than the original one, is restricted in the regions near the coil centers in both the two- and three-dimensional cases. About 40% mitigation of total wall heat flux and nearly 60% drag increment are observed in the three-dimensional cases. By changing the switch states of the coils in the different regions, an additional aerodynamic force can be generated for the adjustment of flight attitude and trajectory. Hence, the magnetic induced vortex provides an effective MHD flow control method for reentry vehicles.

提出了一种基于磁感应涡流的新型磁流体动力学（MHD）流控制机制，以提高回程飞行器的热防护性能和空气动力学性能。设计基于多边形线圈栅格的磁场以获得不同的涡旋形式。建立了五个洛伦兹力模型以揭示磁感应涡旋的MHD相互作用机理。通过数值求解低磁雷诺数方程，获得具有不同涡旋形式的二维圆柱和三维球的流场。在圆柱体的侧面和头部区域分别发现了两种涡流形式。在涡旋的影响下，高的热通量可能会比原来的高，在二维和三维情况下，限制在线圈中心附近的区域。在三维情况下，总壁热通量减少了约40％，阻力增量增加了近60％。通过改变不同区域中的线圈的开关状态，可以产生附加的空气动力来调节飞行姿态和轨迹。因此，磁感应涡流为再入飞行器提供了有效的MHD流量控制方法。