Experimental research on the influence of turbulence intensity on boundary layer transition in Mach 3 supersonic flow
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摘要: 针对超声速来流湍流度（Tu）对转捩影响风洞试验数据缺乏的现状，开展了马赫数（Ma）3条件下不同来流湍流度对平板模型边界层转捩影响的试验研究。在中国空气动力研究与发展中心0.3 m×0.3 m跨超声速风洞（FL-24y）上，通过改变风洞稳定段内稳流参数，形成了来流湍流度在0.82%-1.63%范围内的变化。利用干涉瑞利散射技术测量了来流湍流度，利用红外热图技术测量了平板模型表面温度分布，得到了来流湍流度对转捩起始位置（Fonset）和转捩结束位置（Fend）影响的试验数据。根据试验来流条件，采用γ-Reθ转捩模型仿真了平板模型边界层转捩，并将仿真结果与风洞试验数据做了对比。结果表明：平板模型转捩试验测量结果和数值计算结果符合较好，两种方法得到的转捩起始位置相对误差≤2%，转捩结束位置相对误差≤5%。该试验结果可以为研究超声速来流湍流度对边界层转捩的影响规律提供数据支撑。Abstract: There is still a shortage of the experimental research of boundary layer transition in compressible flows nowadays due to the difficulty in measuring the turbulence intensity. Aiming at studying the influence of the turbulence intensity on supersonic boundary layer transition, a plate model is tested in a blow-down facility （FL-24y of CARDC） at Mach 3. The turbulence intensity of the flow is changed by adjusting the arrangements in the stabilization section of the wind tunnel, which covers a range from 0.82% to 1.63%. The turbulence intensity is measured by interferometric Rayleigh scattering, while the boundary layer transition is derived by infrared thermography. The CFD simulation of the plate model transition is conducted based on the γ-Reθ transition model. The results show that the transition onset position （Fonset） and transition end position （Flength） obtained by the experiment and the simulation agree well, with the maximum relative error coefficient of 2% in Fonset and of 5% in Flength, which provides support to gain a deeper insight into the boundary layer transition mechanism in supersonic flows.
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图 3 湍流度与边界层转捩测量光路布局
Figure 3. Optical arrangement of turbulence intensity and boundary layer transition measurement
图 5 工况1-5测得的平均速度和湍流度结果
Figure 5. Result of turbulence intensity and velocity measurement
图 6 平板边界层转捩红外图像
Figure 6. Infrared thermography image of the boundary layer transition
图 7 工况4转捩三车次重复性测量结果
Figure 7. Repeatability measurement result of the boundary layer transition under flow condition 4
图 9 来流湍流度对壁面摩擦系数影响的计算结果
Figure 9. Calculation result of turbulence intensity on skin fraction coefficient Cf
表 1 试验参数
Table 1. Flow conditions
工况 烧结丝网数/层 阻尼网数/层 Pt/kPa Tt/K 1 2 5 470 293 2 2 3 471 293 3 1 5 470 293 4 1 3 470 293 5 0 5 471 293 
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表 2 试验结果与数值计算结果对比
Table 2. Comparison between experimental result and CFD simulation
Tu/% Fonset/mm Fend/mm 试验值 计算值 e 试验值 计算值 e 0.82 21.29 20.87 −1.97% 43.88 43.34 −1.23% 1.14 20.54 20.26 −1.36% 41.93 42.52 1.41% 1.63 17.92 18.27 1.95% 39.83 41.67 4.62% 注：相对误差e=（计算值−试验值）/试验值×100%
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