中文摘要：

高超声速飞行器MHD（磁流体动力学）斜激波控制应用的关键在于理解等离子体斜激波流场与磁场的相互作用规律，这里发展了全MHD数值模拟方法对其进行研究，数值方法基于八波方程附加源项形式，进行有限体积离散，采用了Roe求解器、OC-TVD空间格式和LU-SGS方法，且采用投影方法降低磁场伪散度误差。考察外加均匀磁场的马赫10无粘导电拐角流动，压缩角为10°。结果中散度误差较低，并且通过激波参数验证了结果的准确性。流场显示，磁场使得激波角增大，部分情况下出现了快、慢激波结构，其中快激波变化更明显；壁面压强根据磁场的不同出现了不同程度的降低。最后采用群速度图方法进行了快慢激波形式分析，解释了磁场影响下流场形式变化机理。

英文摘要：

It is critical to understand mechanism interaction between magnetic field and flow field with oblique shocks in order to take advantage of the MHD flow control of oblique shocks. A full-MHD numerical investigation for Ma = 10 hyprsonic flow over a perfectly conducting corner was carried out. The corner compression angle is 10°. Eight-wave equations were sloved by basic scheme, with the addition source term concerning magnetic field divergence △↓ · B. A 3D Roe solver by means of finite volume formulation, OC-TVD scheme and LU-SGS method were applied in this simulatin. Projection scheme was used to reduce △↓ · B error and the effect is dramatic. There is a fast-slow shock structure in the field in some cases. The magnetic field results in a decrease in the ramp pressure and an increase in shock angle. The fast shock is more sensitive to the magnetic field. Finally, magnetosonic wave velocity and group velocity diagram were used for theoretical analyses, which explain the mechanism of oblique shock variations.