The flow over a wing model with aspect ratio 2 and based on the supercritical airfoil (OAT15A) was experimentally investigated for a fixed Reynolds number (\(Re_\textrm{c}\)) of \(3\times 10^{6}\) and numerous aerodynamic conditions. The angle of attack (AOA) and the Mach number (\(M_\mathrm {\infty }\)) were varied between 5\(^{\circ }\) and 6.5\(^{\circ }\), and between 0.72 and 0.75, respectively. Here we focused on the dynamics of the shock front at incipient and developed buffet conditions, by employing background-oriented schlieren measurements on the wing’s upper surface. The spanwise variations of the shock front statistics and its frequency content were examined. The shock oscillations appeared to be the superposition of multiple fluid modes, of which the most dominant was the classic 2-D buffet, which induced uniform chordwise oscillations of the shock front. The hypothesis was formulated that the remaining modes are linked to physical phenomena reported in the literature, namely the side-wall boundary layer and the vortices detected in the mid-span separated flow.

对展弦比为 2 且基于超临界翼型 (OAT15A) 的机翼模型上的流动进行了实验研究，固定雷诺数 ( \ (Re_\textrm{c}\) ) 为\(3\times 10^{6} \)和许多空气动力学条件。迎角 (AOA) 和马赫数 ( \(M_\mathrm {\infty }\) ) 在 5 \(^{\circ }\)和 6.5 \(^{\circ }\)之间变化，并且分别在 0.72 和 0.75 之间。在这里，我们通过在机翼上表面采用面向背景的纹影测量，重点研究了初始和发展的抖振条件下激波前沿的动力学。检查了激波前沿统计数据的展向变化及其频率内容。激波振荡似乎是多种流体模式的叠加，其中最主要的是经典的二维抖振，它引起激波前缘的均匀弦向振荡。假设剩余模式与文献中报道的物理现象有关，即侧壁边界层和中跨分离流中检测到的涡流。