An experimental investigation has been conducted on swept impinging oblique shock/boundary-layer interactions at a nominal Mach number of 2.28 with a fully turbulent incoming boundary layer ($R{e}_{\theta }=5500$). The swept impinging oblique shock is induced by shock generators with $x\text{-}y$ plane deflection angle $\theta =12.5\mathrm{deg}$ and various $x\text{-}z$ plane sweep angles $\psi =15.0$, 22.5, 30.0, and 40.0 deg. Oil flow visualization, mean pressure measurements, and high-bandwidth pressure transducers are used to provide detailed characterization of the mean and unsteady features of the shock/boundary-layer interactions. Large-scale separation is observed in all cases with spanwise growth especially evident at high shock generator sweep angles. Near the onset of separation in the central region of the tunnel (quasi-infinite span zone), mean pressures are independent of span and scale cylindrically. However, mean pressures at reattachment for higher sweep angles display mild spanwise dependence, suggesting the overall mean flow topology of the shock/boundary-layer interaction is conical. Unsteady pressure measurements beneath the separation shock foot show clear low-frequency unsteadiness, orders of magnitude below that of the incoming boundary layer. As the sweep is increased, the frequency of the separation shock motion is also increased. Specific analysis of the $\psi =30.0\mathrm{deg}$ configuration shows spanwise accelerating ripples of relatively constant frequency that propagate along the shock foot, suggesting that the wavelength of these ripples increases with span. Considerable coherence for this rippling motion is observed in the range associated with the low-frequency unsteadiness of the shock foot. Minimal influence of the incoming turbulent boundary layer on the low-frequency unsteadiness is present, suggesting an unsteadiness mechanism within the shock/boundary-layer interaction.

已经进行了实验研究，以2.28的标称马赫数扫掠撞击斜向冲击/边界层相互作用，并完全扰动了进入边界层（$\mathrm{[R}{Ë}_{\theta }=5500$）。冲击发生器产生扫掠冲击斜斜$X\text{--}ÿ$ 平面偏转角 $\theta =12.5度$ 和各种 $X\text{--}ž$ 平面扫角 $\psi =15.0$，22.5、30.0和40.0度 油流可视化，平均压力测量和高带宽压力传感器用于提供冲击/边界层相互作用的平均和不稳定特征的详细表征。在所有情况下都观察到大规模的分离，并且沿展宽方向增长，尤其是在高冲击波发生器扫掠角下很明显。在隧道中心区域（准无限跨度区域）开始分离的附近，平均压力与跨度和圆柱度无关。但是，对于较大的后掠角，重新安装时的平均压力显示出较小的跨度依赖性，这表明冲击/边界层相互作用的总体平均流量拓扑是圆锥形的。分离电击脚下方的不稳定压力测量结果显示出明显的低频不稳定，比进入的边界层低几个数量级。随着扫掠的增加，分离冲击运动的频率也增加。具体分析$\psi =30.0度$该配置显示沿冲击脚传播的频率相对恒定的展向加速波纹，这些波纹的波长随跨距增加。在与电击脚的低频不稳定相关的范围内，观察到该波动的相当大的连贯性。存在进入的湍流边界层对低频不稳定的最小影响，这表明在冲击/边界层相互作用中存在不稳定机制。