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壁面渗透气膜是一种有应用前景的高超声速边界层转捩控制和减阻降热方式。在马赫数6高超声速静音风洞内，使用纳米粒子示踪的平面激光散射（nano-tracer planar laser scattering，NPLS）技术和高频脉动压力测试技术，研究了壁面渗透气膜工质（氦气、空气和二氧化碳）在相同体积流量条件下对圆锥高超声速边界层的影响。实验结果表明，壁面渗透气膜显著增厚了边界层，最厚位置都出现在渗透区域下游边界处，且氦气气膜时边界层最薄，二氧化碳气膜时最厚。通常，空气气膜和二氧化碳气膜使得边界层内提前出现规则的绳状交织的第二模态波结构，但体积流量较大条件下二氧化碳气膜时，扰动波结构类似剪切层不稳定性。氦气气膜时，扰动波结构不是第二模态波，其形状不规则，随时空变化较大，壁面脉动压力功率谱密度没有出现峰值频率。空气气膜时第二模态波波长大约是边界层厚度的2~3倍，而二氧化碳气膜时增大到3倍以上。二氧化碳气膜时第二模态波峰值频率最小，频带范围最窄，波长最长，幅值最大，扰动波传播距离较远且非线性相互作用较强。Wall-seeping gas film (WSGF) represents a promising method for transition control, drag reduction, and heat reduction in hypersonic vehicles. Experiments were conducted in a Mach 6 hypersonic quiet wind tunnel using nano-tracer planar laser scattering (NPLS) and high-frequency fluctuating pressure measuring techniques. This paper investigates the effects of wall-seeping helium, air, and carbon dioxide gas films under identical volume flow rate conditions on conical boundary layer thickness, disturbance wave structure, wavelength, frequency, amplitude, and nonlinear interaction. The experimental results reveal that WSGF significantly thickens the hypersonic boundary layer, with the thickest position appearing at the downstream boundary of the seeping zone. The boundary layer thickness is thinnest for helium gas film and thickest for carbon dioxide gas film. Generally, air gas film and carbon dioxide gas film induce the appearance of regular, rope-like, and interlaced second-mode waves in advance in the boundary layer. However, under a higher volume flow rate for carbon dioxide gas film, the disturbance wave structure resembles interface fluctuations, with a characteristic wavelength of approximately 18 mm and a peak frequency as low as about 35 kHz, without the rope-like interlaced characteristic. At this time, the influence of shear layer instability becomes significant. The disturbance waves do not exhibit second-mode wave characteristics for wall-seeping helium gas film, whose shape is irregular and undergoes deformation over time and space. Additionally, the power spectral density of wall fluctuating pressure exhibits insignificant variation with volume flow rate and flow direction, which is similar to the characteristics of power spectral density in the laminar boundary layer and has no peak frequency. The wavelength of second-mode waves is about 2~3 times the boundary layer thickness for air gas film while increasing to more than 3 times for carbon dioxide gas film. Compared to air gas film, the application of carbon dioxide gas film results in a smaller peak frequency and bandwidth of disturbance waves, larger characteristic wavelength and amplitude, longer propagation distance, and stronger nonlinear interaction. In the future, attention should be directed towards understanding disturbance wave characteristics in the boundary layer for helium gas film and shear layer instability under larger volume flow rates.
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Keywords:
- Hypersonic boundary layer /
- Wall-seeping gas film /
- Second-mode waves /
- NPLS
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