面向高超声速，传统的激波边界层干扰显现出新的特点。一方面，超燃冲压发动机作为吸气式高超声速推进的最佳备选动力装置，其内部的激波边界层干扰会受到肩部膨胀波系的影响；另一方面，高超声速导致的真实气体效应也会对激波边界层干扰产生影响。然而目前复杂因素影响下的激波/边界层干扰还没有系统性的研究，因此有必要开展相关工作，理解膨胀波与真实气体效应对激波边界层干扰的影响机制。

本文利用数值仿真方法研究了复杂因素影响下的激波/边界层干扰特性，获得了膨胀波与真实气体效应的影响规律，并揭示了这两种因素对激波/边界层干扰的影响机制。

首先考察了膨胀波与激波相对位置、膨胀波的分布、入射的激波强度等参数对激波/边界层干扰的影响。研究表明：膨胀波与入射激波的相对位置会严重影响流场特性。随着入射激波从上游不断向下游移动，分离区的尺寸先明显减小后又迅速增大，使得分离区最小的入射激波点位于膨胀角下游2~3个边界层厚度处；膨胀波的不同分布导致了其影响强度以及影响范围的不同。肩部半径越大，膨胀波系越分散，对分离点、再附点的限制越小，使分离区尺寸明显减小的区间也就越大；另外，分离区尺寸受入射激波强度的影响非常大，随着激波强度的不断减小，分离区的尺寸迅速减小，可以有效抑制分离区尺寸的位置区间就越大。随后，发现仅采用无黏分析压比无法正确关联膨胀波影响下的激波边界层干扰，分离区尺度与黏性流压比呈现正相关关系：当激波入射点打在肩部附近时，产生的压比最小，对应的分离区的尺寸也最小；最后在分离区特征标度与无量纲压升之间建立了联系，发现在肩部上游膨胀波影响较小处，不同肩部半径的数据均坍缩到一起，标度律的效果较好；在受到肩部膨胀波的影响后，原来的标度律效果变差。

采用四种气体模型研究了真实气体效应对激波边界层干扰的影响。首先分析了真实气体效应下SWBLI流动的典型特征，研究表明：在Ma15的情况下，不同气体模型下的激波边界层干扰特性有很大差异。真实气体效应包括化学非平衡与热力学非平衡两种，其对于分离区尺寸的影响相反。离解反应发生在边界层和分离区内，能够降低边界层内的温度并且使得边界层更薄，从而使得两种化学反应气体的分离区尺寸更小。相比于化学非平衡气体，热化学非平衡气体由于振动能的不平衡，导致壁面温度更高，分离区尺寸更大。然后，进一步考察了来流马赫数与壁面温度的影响。结果表明：来流马赫数与壁面温度的降低均能够使得流场中的化学反应程度急剧下降，化学非平衡的影响减弱，导致化学非平衡气体与热完全气体的流动特性非常接近，而热力学非平衡的作用在更广泛的条件下影响显著。最后，对热力学非平衡的影响区域进行了讨论。

For hypersonic flow, the traditional shock boundary layer interaction exhibits new features. In hypersonic flow, the shock boundary layer interaction inside the scramjet will be affected by the shoulder expansion wave system; And in the meanwhile, the real gas effect caused by hypersonic will also affect the shock boundary layer interaction. At present, the impacts of complex factors, such as, ... , upon the shock/boundary layer interaction has not been systematically conducted., so it is necessary to carry out relevant work to understand the impact mechanism of expansion wave and real gas effects on shock boundary layer interaction.

In this work, the characteristics of shock wave/boundary layer interaction under the influence of complex factors are numerically investigated, the effects of expansion wave and real gas are analyzed, and the underlying mechanism of these two factors on shock wave/boundary layer interaction is revealed.

Firstly, the effects of the relative position of the expansion wave and the shock wave, the distribution of the expansion wave, and the intensity of the incident shock wave on the shock/boundary layer interaction are investigated. Research has shown that the relative position of the expansion wave and the incident shock wave can affect the flow field characteristics seriously. As the incident shock wave moves from upstream to downstream, the size of the separation zone decreases significantly at first and then increases rapidly, so that the smallest incident shock point in the separation zone is located at 2-3 boundary layer thicknesses downstream of the expansion wave; The different distribution of expansion waves leads to differences in their intensity and range of influence. The larger the radius of the shoulder, the more dispersed the expansion wave system, and the smaller the restrictions on separation points and reattachment points, resulting in a larger range of significant reduction in the size of the separation zone; In addition, the size of the separation zone is greatly affected by the intensity of the incident shock wave. As the shock wave intensity continues to decrease, the size of the separation zone decreases rapidly, and the range of positions that can effectively suppress the size of the separation zone becomes larger. Subsequently, it was found that the shock boundary layer interaction under the influence of expansion waves could not be correctly correlated only by using the inviscid analysis pressure ratio, and the separation zone scale was positively correlated with the viscous flow pressure ratio: when the shock wave incident point hit near the shoulder, the pressure ratio generated was the smallest, and the corresponding separation zone size was also the smallest; Finally, a connection was established between the characteristic scaling of the separation zone and the dimensionless pressure rise. It was found that at the location where the upstream expansion wave had a small impact on the shoulder, the data of different shoulder radii collapsed together, and the scaling law had a better effect; After being affected by shoulder expansion waves, the original scaling law effect deteriorates.

Four gas models are used to study the influence of real gas effects on shock boundary layer interaction. Firstly, the typical characteristics of SWBLI flow under the effect of real gas are analyzed. The research shows that in the case of Ma15, the shock boundary layer interaction characteristics using different gas models changes significantly. The real gas effect includes two types: chemical non equilibrium and thermodynamic non equilibrium, which have opposite effects on the size of the separation zone. The dissociation reaction occurs in the boundary layer and the separation zone, which can lower the temperature in the boundary layer and make the boundary layer thinner, thus making the separation zone of the two chemical reaction gases smaller. Compared to chemical non-equilibrium gases, thermochemical non equilibrium gases shows higher wall temperatures and larger separation zone sizes due to the imbalance of vibration energy. Then, the influence of incoming Mach number on wall temperature was further investigated. The results show that the decrease of incoming Mach number and wall temperature can make the chemical reaction degree in the flow field drop sharply, and the influence of chemical non-equilibrium is weakened, resulting in the flow characteristics of chemical non-equilibrium gas and thermal Perfect gas very close. The non-equilibrium effects of thermodynamics have a significant impact on a wider range of conditions. Finally, the influence regions of thermodynamic non-equilibrium were discussed.