The effects of static surface deformations on a spatially developing supersonic boundary layer flow at Mach number $M=4$ and Reynolds number $R{e}_{{\delta }_{in}}\approx 49300$, based on inflow boundary layer thickness (${\delta }_{in}$), are analyzed by performing large eddy simulations. Two low-order structural modes of a rectangular clamped surface panel of dimensions $\approx 33{\delta }_{in}\times 48{\delta }_{in}$ are prescribed with modal amplitudes of ${\delta }_{in}$. The effects of these surface deformations are examined on the boundary layer, including changes in the mean properties, thermal and compressibility effects and turbulence structure. The results are analyzed in the context of deviations from concepts typically derived and employed for equilibrium turbulence. The surface deflections, to some degree, modify the correlations that govern both Morkovin’s hypothesis and strong Reynolds analogy away from the wall, whereas in the near-wall region both the hypotheses breakdown. Modifications to the turbulence structure due to the surface deformations are elucidated by means of the wall pressure two-point correlations and anisotropy invariant maps. In addition to the amplification of turbulence, such surface deformations lead to local flow separation, instigating low-frequency unsteadiness. One consequence of significance to practical design is the presence of low frequency unsteadiness similar to that encountered in impinging or ramp shock boundary layer interactions.

静态表面变形对马赫数下空间发展的超音速边界层流的影响 $米=4$ 和雷诺数 $\mathrm{电阻}{\mathrm{电子}}_{{\delta }_{\mathrm{一世}n}}\approx 49300$, 基于流入边界层厚度 (${\delta }_{\mathrm{一世}n}$)，通过执行大涡模拟进行分析。尺寸矩形夹紧面板的两种低阶结构模态$\approx 33{\delta }_{\mathrm{一世}n}\times 48{\delta }_{\mathrm{一世}n}$ 规定了模态振幅 ${\delta }_{\mathrm{一世}n}$. 检查这些表面变形对边界层的影响，包括平均属性的变化、热和压缩性影响以及湍流结构。结果在偏离通常为平衡湍流导出和使用的概念的背景下进行分析。表面偏转在某种程度上修改了控制 Morkovin 假设和远离壁面的强雷诺类比的相关性，而在近壁区域，这两个假设都失效了。由于表面变形对湍流结构的修改通过壁压力两点相关性和各向异性不变图来阐明。除了湍流的放大，这种表面变形会导致局部流动分离，引发低频不稳定。