Review of research on the receptivity of hypersonic boundary layer
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摘要: 高超声速边界层感受性是边界层转捩预测与控制的关键环节,其对高超声速飞行器研究至关重要。目前关于高超声速边界层感受性的实验研究仍然十分匮乏,为了更好地理解高超声速边界层感受性过程并指导该领域的实验研究,文章梳理了近20年来国际上高超声速边界层感受性问题的研究内容,包括对自由流扰动和壁面扰动的感受性,并主要介绍了Fedorov的前缘感受性理论和模态转化机制。最后总结了自由流扰动中感受性的不同发展路径。Abstract: As a key aspect of transition prediction and control, receptivity process in hypersonic boundary layer is of great importance. However, it still has not been thoroughly understood, and is especially lacking in experimental verification. In this paper, two categories of disturbances are reviewed, namely, free-stream disturbance (acoustic, vertical, thermal perturbation, shock wave and particulates) and wall-induced disturbances (roughness, vibration, blowing and suction, surface heating and cooling). Mostly concerned are the theory of Fedorov about leading-edge receptivity and inter-modal exchange mechanism. In order to make the issue of receptivity more clearly understood, a compendious path diagram is sketched to describe paths to Mack modes.
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Key words:
- hypersonic boundary layer /
- receptivity /
- review /
- theory research /
- acoustic /
- roughness /
- wall temperature
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图 3 二维扰动的相速度和增长率随雷诺数变化
Figure 3. Phase speed of two-dimensional disturbances as a function of Reynolds number[38]
图 5 声波感受性示意图
Figure 5. Physical picture of receptivity to acoustic waves[38]
表 1 壁面温度对感受性及转捩的影响
Table 1. Effect of wall condition on transiton and receptiviy
研究者 模型 Ma 方法 壁面条件 结论 Fedrov et al.2003 平板 6 理论 绝热 感受性:慢声波/快声波≈50 冷壁 快模态可能失稳 Ma & Zhong2001 平板 4.5 计算
DNS绝热 等温比
绝热对声波的感受性小等温 Balakumar2015 楔形圆锥 6 计算 绝热 感受性:慢声波/快声波≈20 冷却 冷却 (尖锥):转捩提前 Kara et al.2007,2008 楔形直锥 6 计算 绝热 感受性:慢声波/快声波≈67 冷却 冷却时转捩提前 Blanchard 1995 裙锥 6 实验 绝热/冷却 冷却时转捩提前 Demetriades 1978 直锥 8 实验 Tw: 0.41~0.8 冷却时转捩提前 Lysenko & Maslov 1984 平板 2/4/6 实验 Tw: 0.3~1 冷却对声波没影响Mack第一模态稳定第二模态失稳 Stetson et al. 1989 直锥 8 实验 Tw=0.42 冷却时转捩提前Mack第二模态频率变高,增长率变大 Polivanov2011 平板 5.4 理论计算 冷却加热 冷却时转捩提前冷却位置影响转捩 Sidorenko et al. 2015 直锥 6 实验计算 局部冷却 抑制第二模态转捩延迟 局部加热 与局部冷却结果相反 Soudakov et al.2009 平板 6 计算DNS 温度跳跃 温度跳跃影响感受性 Sanator et al. 1965 尖锥 8.8 实验 Tw: 0.08~0.4 没有明显影响 注:Tw指壁面温度/绝热温度 -
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