激波干扰是高超声速飞行器气动布局和超燃冲压发动机设计中需重点考虑的局部干扰现象，当该现象发生时会产生复杂的波系结构，对流场行为特征产生影响，进而对飞行器物面载荷及发动机性能产生显著影响。采用数值计算方法针对斜激波入射平板问题，在固定来流马赫数5、单位雷诺数7.12×106 m-1不变的条件下，通过改变上下平板展向宽度研究了6个不同状态下的激波反射类型。结果表明在受限空间内必须考虑侧向溢流对激波反射类型的影响。随平板展向宽度增加，激波反射类型从正则反射逐渐过渡至马赫反射，且马赫杆长度变长并逐渐前移，直至导致内流道堵塞形成脱体激波。采用激波极曲线方法在激波入射角度固定的条件下对两种激波干扰类型的产生机制进行了分析，发现随激波强度增加两束透射激波极曲线上移缩小，进而造成波后流场参数匹配需求，激波反射类型逐渐从正则反射向马赫反射转变，得到了与数值计算结果一致的结论。
Shock wave interference is a local interference phenomenon that needs to be considered in the pneumatic layout of hypersonic vehicle and the design of scramjet. When this phenomenon occurs, complex wave structures will be generated to affect the behavior characteristics of the flow field and then significantly affect the planeload and engine performance. Numerical simulation is used to study the problem of incident shock wave of a plate. Under the condition of constant Mach number 5 and unit Reynolds number 7.12×106 m-1, the types of shock reflection in six different states are studied by changing the transverse width of the upper and lower plates. The results show that the influence of lateral overflow on the reflection types of shock wave must be considered in the restricted space. With the broadening of the transverse width of the plate, the shock reflection type gradually changes from regular reflection to Mach reflection, and the length of Mach stem becomes longer and moves forward gradually until the inner channel is blocked and the detached shock wave is formed. The shock polar theory is also used to analyze the generation mechanism of the two shock interference types under the condition of a fixed shock angle. The analysis shows that with the increase of shock wave intensity, the two transmission shock pole curves move upward and shrink, which leads to the requirement for parameter matching of the flow field behind the wave. The shock reflection type gradually changes from regular reflection to Mach reflection, and the conclusion is consistent with the numerical calculation and wind tunnel test results.
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