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摘要:
激波与湍流边界层相互干扰(SWTBLI)现象可诱导形成复杂的流场结构和气动力热分布特性，其干扰机制和影响机理至今仍未被充分掌握。为分析超/高超声速SWTBLI流动的机理，开展了来流马赫数为3、5、11条件下压缩拐角流动的直接数值模拟(DNS)研究。结果显示，SWTBLI使干扰区内的速度、压强等物理量的脉动显著增强，且增强幅值随来流马赫数升高而增大；同时，上游边界层中的温度、压强等物理量的脉动也随来流马赫数的增大而增强。在SWTBLI作用下，流动的可压缩效应明显增强，干扰区内压力膨胀项和膨胀耗散项不再可忽略。在高超声速条件下，上游边界层中的压力膨胀项和膨胀耗散项也比较重要。此外，SWTBLI诱导的壁面压强平均值和脉动均方根值的分布存在共性。在所有来流马赫数下，干扰区内的壁面压强脉动相比上游边界层均显著增强，并形成明显的峰值。流动发生显著分离时，将分别形成位于平均分离点和再附点附近的壁面压强脉动峰值。
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关键词:
- 激波与湍流边界层相互干扰 /
- 高超声速流动 /
- 可压缩湍流 /
- 直接数值模拟 /
- 分离流
Abstract:The shock-wave/turbulent-boundary-layer interaction (SWTBLI) phenomenon will result in complex flow structures. Direct numerical Simulation (DNS) studies of compressible corner flow under freestream mach number 3, 5, 11 conditions have been carried out to further explore supersonic/hypersonic SWTBLI flow mechanisms. It is found that SWTBLI causes a significant increase of turbulence fluctuation in the interaction zone, and such influence is further enhanced with the increase of freestream Mach number. Higher Mach numbers also make variations in pressure and temperature in the upstream turbulent boundary layer more noticeable. In addition, the compressible effect is also significantly enhanced by SWTBLI. Terms associated with compressible effects, including the pressure dilatation and dissipation terms, are no longer insignificant in the interaction zone and the upstream boundary layer (in the case of hypersonic travel). Furthermore, commonalities of SWTBLI-induced mean and RMS wall pressure distribution are observed. Both mean and RMS wall pressure increase rapidly through the interaction zone until reaching their peak values. Distribution of RMS wall pressure along streamwise direction shows two peak value points when a large separation zone forms, which are closely related to the mean separation point and mean reattachment point, respectively.
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图 1 超声速压缩拐角流动实验模型和计算网格
Figure 1. Experimental models and computational grids for supersonic compression corner flow
图 7 Ma∞=11算例瞬时温度云图
Figure 7. Instantaneous temperature gradient contour of Ma∞=11 case
图 9 不同流场区域流向脉动速度分布结果
Figure 9. Distributions of fluctuation velocity in different flow regions
图 10 上游边界层脉动速度结果对比
Figure 10. Comparison of fluctuation velocity in upstream boundary layer
图 11 上游边界层温度脉动结果对比
Figure 11. Comparison of fluctuation temperature in upstream boundary layer
图 12 上游边界层密度脉动结果对比
Figure 12. Comparison of RMS density profile in upstream boundary layer
图 13 不同来流马赫数下壁面压强脉动结果对比
Figure 13. Comparison of fluctuation wall pressure results under different Mach numbers
图 14 不同流场区域可压缩效应项分布
Figure 14. Distribution of compressible effect terms in different flow field regions
表 1 边界层参数计算和实验结果对比
Table 1. Comparison of boundary layer parameters between CFD and experimental results
变量 实验测量值 DNS计算结果 Maδ 2.9 2.9 Reθ 2400 2450 δ/mm 6.7 6.7 δ*/mm 2.36 2.6 θ/mm 0.43 0.48 H=δ*/θ 5.49 5.41 Cf 2.17×103 2.20×103 uτ 32.9 30 
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表 2 不同DNS算例的计算域和网格尺寸
Table 2. Computation domain and grid size of different DNS cases
Ma∞ 流向计算
域长度避面法向计算
域长度展向计算
域长度Δx+ Δz+ Δy1 + 3 27δ 6δ 2δ 5~7 6 0.3 5 12δ 3δ 2δ 5~10 8 0.15 11 40δ 4δ 2δ 5~10 8 0.3
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表 3 不同算例平均分离区长度和平均分离点、平均再附点位置
Table 3. Length of separation zone and position of average separation and reattachment point
Ma∞ 平均分离点
位置 (x*/δ)平均再附点
位置 (x*/δ)平均分离区
长度 (x*/δ)3 −2.7 0.8 3.5 5 −1.7 0.9 2.6 11 −0.6 0.2 0.8
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