Crossing shock waves/transitional boundary layers interactions in the double vertical wedges configuration
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摘要: 针对超声速双垂直楔构型产生的交叉激波与转捩边界层干扰现象，结合风洞试验与数值模拟进行了深入研究。试验在中国空气动力研究与发展中心Φ 600 mm脉冲燃烧风洞中开展，来流马赫数3.0，单位雷诺数2.1×106 m−1，获得了流场纹影、壁面压力和壁面热流。结果表明：受交叉激波逆压梯度作用，层流边界层在激波交汇附近产生分离，并在干扰区迅速转捩；在上游安装斜坡型涡流发生器或粗糙带，诱导边界层在干扰前转捩为湍流，分离区被有效抑制，干扰区热流明显下降（热流峰值下降超过25%）。数值模拟和风洞试验得到的激波结构、壁面压力吻合良好，但壁面热流计算值明显大于试验值。对比转捩模型和湍流模型计算结果发现：明显偏高的湍流黏性系数是RANS方法在非分离区过高预测干扰区热流的主要原因。Abstract: Study on crossing shock waves/transitional boundary layer interaction in the double vertical wedges configuration was carried out using wind tunnel tests and numerical calculations. The wind tunnel tests were carried out at Φ 600 mm pulse combustion wind tunnel. The Mach number of the free stream condition is 3.0, and the unit Reynolds number is 2.1×106 m−1. The schlieren images, wall pressure and wall heat fluxes were obtained during the tests. The results show that because of the adverse pressure gradient caused by the crossing shock waves, the separation of the laminar boundary layer was captured near the shock waves intersection point. And the transition from laminar to turbulent occurred rapidly in the interaction region. After installation of vertex generator devices or roughness devices, the boundary layer transition position moved to the upstream of the interaction region, the separation was effectively inhibited. And the heat fluxes in the interaction region declined obviously. The peak value of heat fluxe was reduced by more than 25%. The shock wave structures and wall pressure distributions obtained from tests and simulations agreed well, while the prediction heat fluxes were much larger than the test results. The comparison between the calculated results of the transition model and the turbulence model shows that the obviously larger turbulence viscosity is the main reason why RANS methods over-predict the heat fluxes in the unseparated interaction region.
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Key words:
- crossing shock waves /
- shock waves/boundary layer interaction /
- turbulence /
- transition
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图 4 E型同轴热电偶典型标定信号和标定结果
Figure 4. Calibration signal and results of type E coaxial thermocouple
图 6 采用不同网格计算得到的壁面压力和热流分布
Figure 6. Heat fluxes and pressure distribution calculated using different grids
图 7 计算得到的x=–120 mm处边界层内速度分布
Figure 7. Velocity distribution of the x=–120 mm boundary layer by calculation
图 12 试验与计算壁面热流分布对比
Figure 12. Heat flux distributions obtained from test and calculation
图 13 转捩模型计算得到的不同z截面γ分布
Figure 13. Contours of γ in different z constant planes obtained by transition model
图 15 计算得到的底板壁面热流云图
Figure 15. Calculated contours of heat fluxes in the base flat plate
图 17 计算得到的底板壁面压力云图及摩擦力线分布
Figure 17. Calculated contours of pressure in the base flat plate
表 1 试验来流条件
Table 1. Freestream condition of the test
马赫数 总温
Tt/K总压
pt/MPa单位雷诺数
Re/（106 m−1）来流组分摩尔比
（O2∶N2∶H2O）比热比 3.0 1350 0.335 2.1 0.21∶0.56∶0.23 1.34 
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表 2 x>0区域x、y、z方向上网格数
Table 2. Grid numbers in x, y, z directions in the x>0 area
网格 nx ny nz 粗网格（rough） 141 81 71 基准网格（base） 201 121 101 密网格（fine） 401 181 151
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