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摘要:
高超声速边界层转捩会使壁面摩阻和热流显著增加，严重影响飞行器的性能。微孔隙表面在不明显改变平均流场的同时，能够有效抑制边界层转捩，具有较大的应用潜力。在马赫数为6 的Ludwieg 管风洞中研究泡沫碳孔隙材料对尖锥边界层中不稳定波的影响规律，试验结果表明：尖锥边界层存在明显的第2模态波，其特征频率随着流向位置增加而减小。相比于光滑表面，泡沫碳表面使不同流向位置上的第2模态波增长率均有明显下降，至少延长第2模态传播区域21.6%。此外，采用阻抗管测量泡沫碳表面的声学特性获取阻抗模型系数，并结合线性稳定性理论预测了泡沫碳表面扰动模态增长率，理论结果与试验结果变化趋势相同。
Abstract:Hypersonic boundary-layer transition generates a significant increase in skin friction and heat flux, which leads to severe restrictions on the performance of hypersonic vehicles. Micropore surfaces have a significant deal of potential for application since they can successfully prevent boundary layer transition without clearly altering the average flow field.The effects of carbon foam material on unstable modes in hypersonic boundary-layer are studied in Mach 6 Ludwieg wind tunnel, the experimental results indicate that there exists an obvious second mode wave in the boundary layer, and its characteristic frequency decreases downstream. The carbon foam surface, when compared to a smooth surface, at various streamwise positions retards the formation of the second mode wave and increases the second mode propagation area by at least 21.6%. In addition, the impedance tube is used to measure the acoustic characteristics of the carbon foam surface to obtain impedance model coefficients. The linear stability theory is used to predict the growth rate of disturbance mode on the carbon foam surface, and the theoretical results have the same trend as the experimental results.
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图 2 Ludwieg管风洞的归一化压力波动
Figure 2. Normalized pressure fluctuations in Ludwieg wind tunnel
图 8 不同尖锥表面沿流向的功率谱密度
Figure 8. Power spectral density along flow direction of different sharp cone surfaces
图 10 尖锥光滑与泡沫碳表面的增长率
Figure 10. Growth rate between sharp cone smooth surface and foamed carbon surface
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