This paper describes results of an experimental and numerical study of a magnetohydrodynamic (MHD) method for controlling a hypersonic (M = 6) air flow in which a launched device of typical configuration is located. The experiments are carried out using an MHD rig based on a shock tube. The flow in front of the body is ionized using an electric discharge in an external magnetic field with an induction B = 0.80–1.58 T. Conditions corresponding to the experimental conditions are numerically simulated using the Reynolds-average steady Navier-Stokes equations. The MHD interaction region is simulated by isolating a zone in front of the blunt part of the model with given force and heat sources. It is shown that, as a result of strong MHD interaction, the bow shock moves away from the model surface and the heat flux to the body decreases with a value of the Stuart number S = 0.1–0.3.

中文翻译：

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钝体高超声速流动中磁流体动力学相互作用的数值和实验模拟

本文描述了用于控制高超声速 (M = 6) 气流的磁流体动力学 (MHD) 方法的实验和数值研究结果，其中典型配置的发射装置位于。使用基于激波管的 MHD 装置进行实验。身体前方的流动使用外部磁场中的放电电离，感应强度为 B = 0.80–1.58 T。对应于实验条件的条件使用雷诺平均稳态 Navier-Stokes 方程进行数值模拟。MHD 相互作用区域是通过使用给定的力和热源隔离模型钝部分前面的区域来模拟的。结果表明，由于强 MHD 相互作用，