Predicting shock/shock and shock/boundary-layer interactions in gas flows that surround high-speed vehicles is key in aerodynamic design. Under typical hypersonic conditions, these flow structures are influenced by complex nonequilibrium phenomena leading to high-temperature effects. In this work, the conceptual Bedford wing-body vehicle is studied to analyze flow patterns in shock/shock and shock/boundary-layer interactions with thermochemical nonequilibrium. A parametric computational fluid dynamics study is carried out for different hypersonic operating conditions, with respect to the freestream Mach number. Simulations are performed with the SU2-NEMO solver coupled to the Mutation++ library, which provides all the necessary thermodynamic, kinetic, and transport properties of the mixture and chemical species. The Adaptive Mesh Generation library is used for automatic anisotropic mesh adaptation. Numerical results show that increasing the freestream Mach number from 4 to 10 leads to changes in the shock layer, locations of shock impingement, and regions of boundary-layer separation. Despite these changes, the change in freestream Mach number has little impact on the overall shock interaction structures.

预测高速车辆周围气流中的冲击/冲击和冲击/边界层相互作用是空气动力学设计的关键。在典型的高超声速条件下，这些流动结构受到复杂的非平衡现象的影响，导致高温效应。在这项工作中，研究了概念性的贝德福德翼体飞行器，以分析激波/激波和激波/边界层与热化学非平衡相互作用中的流动模式。针对自由流马赫数，针对不同的高超音速操作条件进行了参数化计算流体动力学研究。使用与 Mutation++ 库耦合的 SU2-NEMO 求解器进行模拟，该库提供混合物和化学物质的所有必要的热力学、动力学和传输特性。自适应网格生成库用于自动各向异性网格自适应。数值结果表明，将自由流马赫数从 4 增加到 10 会导致激波层、激波撞击位置和边界层分离区域发生变化。尽管有这些变化，自由流马赫数的变化对整体激波相互作用结构的影响很小。