不同角度压缩斜坡上高速流下方的声学载荷
Acoustic Loading Beneath High-Speed Flow Over a Compression Ramp at Different Angles
AI总结：
通过大涡模拟研究高超声速边界层接近压缩角时的压力波动，改变压缩角，发现均方根壁面压力波动强度随分离强度剧增，还分析了声学载荷、压力事件及频谱能量变化等。
摘要：
进行大涡模拟以表征高超声速边界层接近压缩角时的压力波动。模拟在马赫数6.04和入口动量厚度雷诺数$Re_{\theta}=4340$下进行。压缩角在$10^\circ$、$20^\circ$、$30^\circ$和$34^\circ$之间变化，涵盖附着到强分离状态。研究了压力波动强度、声学载荷等随压缩角的变化情况。
英文摘要：
Large-eddy simulations are performed to characterize the pressure fluctuations beneath a hypersonic boundary layer approaching a compression corner. The simulations are carried out at Mach 6.04 and an inlet momentum-thickness Reynolds number of $Re_θ=4340$. The compression-corner angle is varied over $10^\circ$, $20^\circ$, $30^\circ$, and $34^\circ$ spanning attached to strongly separated regimes. The peak root-mean-square wall-pressure fluctuations intensity increases sharply with separation strength, rising by $312\%$ from R20 to R30 and a further $67\%$ from R30 to R34, with the peak located downstream of reattachment. Notably, acoustic loading increases from 140 dB in the approach flow to $\approx177$ dB downstream of reattachment in the $34^\circ$ case. Further analysis reveals that intense intermittent pressure events are concentrated near the shock foot, spatially distinct from the peak acoustic-loading region, where fluctuations are relatively sustained. With increasing interaction strength, spectral energy shifts from turbulence-dominated high frequencies to broadband low-frequency motion. Band-isolated acoustic loading maps reveal high-frequency fluctuations as the dominant contributor across the interaction zone, with low-frequency fluctuations becoming locally comparable in the R34 case near the separation region. Spatio-temporal maps of bandpass-filtered pressure fluctuations reveal downstream convecting Kelvin-Helmholtz structures and upstream propagating pressure waves near the shock foot.
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