Hypersonic boundary layer transition simulation of complex configuration using γ-Reθ transition model
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摘要: 在大规模并行可压缩Navier-Stokes求解器AHL3D框架上，搭建了γ-Reθ转捩模型。在该模型基础上，通过高超声速二维进气道构型算例，加入了可压缩性修正，使其能够模拟可压缩性对转捩位置的影响，同时通过修改分离诱导转捩关键参数，增加了模型对粗糙颗粒诱导强制转捩的敏感性，最后对耦合关系式也进行了适当的修改。为了验证修改后的模型对高超声速自然转捩和强制转捩的预测能力，对Ma7.4 Ames全尺寸模型和单个粗糙颗粒诱导Ma6的平板转捩进行了模拟。结果表明：与原始模型相比，修改后的模型的转捩位置被大大推迟，并且粗糙颗粒诱导转捩的作用被加强，与实验结果吻合良好。采用此模型对X-51A的20%缩比进气道模型在普渡大学Ma6静音风洞中的试验状态进行了模拟，模型不仅能够反映来流湍流度对转捩的影响，也能反映转捩带对转捩的促进作用。结果显示修改的转捩模型在高超声速复杂构型的转捩预测及研究中具有很好的应用潜力。Abstract: The correlation-based γ-Reθ transition model has been implemented into a large scale parallel compressible Navier-Stokes solver AHL3D. In order to simulate the effects of compressibility of the hypersonic flow, compressible modification has been added into this model. The constant parameter for the separation induced transition has been enhanced to improve the ability of the forced transition simulation. The correlation equations have been adjusted after all the modifications. In order to validate the modified models' ability to capture the transition location, a Ma=7.4 Ames all-body aircraft model for natural transition and a Ma=6 flat plate installed with three dimensional roughness elements for forced transition were simulated. The results show that compared to the original model, the modified model gives much later transition location and stronger effects of the roughness elements, which agree well with the experimental results. Finally, the modified model has been applied to the simulation of hypersonic natural and forced transition of the 20% scale X-51A fore body configuration in BAM6QT. The present model can simulate not only the effects of the free stream turbulence intensity but also the promotion of the transition position by the forced transition trips. The results show the good potential of the modified γ-Reθ transition model in transition prediction for complex configurations in hypersonic flows.
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Key words:
- transition model /
- boundary layer /
- hypersonic inlet /
- forced transition
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图 2 不同计算方法得到的热流分布(case1)
Figure 2. Heat flux distribution of different methods (case1)
图 5 自然转捩热流分布(case1，修正后的模型)
Figure 5. Heat flux distribution of natural transition (case1, modified model)
图 6 自然转捩热流分布(case2，修正后的模型)
Figure 6. Heat flux distribution of natural transition (case2, modified model)
图 7 强制转捩热流分布(case3，修正后的模型)
Figure 7. Heat flux distribution of forced transition (case3, modified model)
图 8 多套网格计算结果(case2，修正后的模型)
Figure 8. Heat flux distribution of three meshes (case2, modified model)
图 12 迎风面的St数分布和摩擦力线
Figure 12. Stanton number distribution and friction force lines of the windward
图 15 红外热试验和计算得到的St数分布(圆柱形粗糙颗粒诱导转捩)
Figure 15. Infra-red visualization and calculated Stanton number distribution for cylinder roughness elements
图 16 红外热试验和计算得到的St数分布(钻石形粗糙颗粒诱导转捩)
Figure 16. Infra-red visualization and calculated Stanton number distribution for diamond roughness elements
图 17 尾迹区和非尾迹区的St数对比
Figure 17. Comparison of St number in and out of wake region for cylinder and diamond roughness elements
图 18 粗糙颗粒下游的流向涡发展情况
Figure 18. Development of stream wise vortex downstream of the roughness elements
图 19 20%缩比X-51A前体构型示意图
Figure 19. Windward side of 20% scale X-51A forebody configuration
图 20 迎风面测量得到的壁面温度和计算得到的摩阻系数(case5)
Figure 20. Measured surface temperature and calculated skin friction for windward surface (case5)
图 21 迎风面测量得到的壁面温度和计算得到的摩阻系数(case6)
Figure 21. Measured surface temperature and calculated skin friction for windward surface (case6)
图 23 中心线上测量得到的壁面温度和计算得到的摩阻系数(case4, case5)
Figure 23. Measured surface temperature and calculated skin friction of the center line (case4, case5)
图 24 中心线上测量得到的壁面温度和计算得到的摩阻系数(case6)
Figure 24. Measured surface temperature and calculated skin friction of the center line (case6)
表 1 二维计算时进气道来流条件
Table 1. Free stream condition for 2-D inlet simulation
Case Ma 总压/
MPa总温/
K迎角/
(°)Re/
(107·m-1)转捩类型 1 5.96 2.00 473.2 1.0 1.82 自然 2 4.97 1.01 357.7 -0.6 2.21 自然 3 5.96 2.00 473.2 1.0 1.82 强制 
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表 2 全尺寸升力体模型风洞试验来流条件
Table 2. Test conditions for the all-body model
Ma Re/m-1 总温/K 静温/K 壁面温度/K 迎角/(°) 7.4 15×106 722 62 300 15
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表 3 20%缩比X-51A构型的试验条件
Table 3. Test conditions for the 20% scaled X-51A forebody configuration
Case Ma Re/m-1 总压/kPa 总温/K 来流湍流度 转捩类型 4 6.00 6.59×106 586 418 0.05% 自然 5 5.80 7.40×106 621 424 3.00% 自然 6 5.78 7.35×106 614 424 3.00% 强制
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