With the development of supersonic/hypersonic vehicles, the influence of non-uniform flow has attracted increasing attention. Non-uniform flow exists everywhere in a scramjet, which is a potent engine for supersonic/hypersonic vehicles. Most flows entering the isolator, combustor, and nozzle exhibit high non-uniformity. Thus, several design methods for generating non-uniform flow have been proposed. However, these design methods cannot simulate flow distortion with high accuracy, especially the non-uniform flow caused by shock wave interaction. Thus, a design method for distortion generators, which can generate non-uniform flow associated with flow deflection angles, is proposed in this study to mimic the shock wave-dominated non-uniform flow with shock wave interaction. Numerical simulation and experiment are adopted to verify the effectiveness and reliability of the proposed method. The Mach number on the outlet and the surface pressure distribution on the upper wall of the distortion generator obtained in the experiment show a good agreement with the target one.

随着超音速/超人车辆的发展，非均匀流动的影响已引起越来越多的关注。超燃冲压发动机中到处都有不均匀的流动，超燃冲压发动机是超音速/超人车辆的强大引擎。进入隔离器，燃烧器和喷嘴的大多数流量表现出很高的不均匀性。因此，已经提出了几种用于产生非均匀流动的设计方法。但是，这些设计方法不能高精度地模拟流动畸变，特别是冲击波相互作用引起的非均匀流动。因此，本研究提出了一种变形发生器的设计方法，该方法可以产生与流动偏转角相关的非均匀流动，以模拟以冲击波相互作用的，以冲击波为主的非均匀流动。通过数值模拟和实验验证了该方法的有效性和可靠性。实验获得的畸变发生器出口处的马赫数和上壁的表面压力分布与目标值良好吻合。