Numerical study on the control of airfoil stall with bio-inspired herringbone groove array
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摘要:
以NACA0012翼型为研究对象，通过数值模拟的方法探究了仿生人字形沟槽阵列对大攻角下翼型失速的控制规律及物理机制。人字形沟槽阵列布置在翼型上表面尾缘，并探究了沟槽深度以及沟槽偏转角对翼型失速控制效果的影响，结果显示：不同设计的人字形沟槽阵列均可以有效拓宽翼型的稳定工作范围，深度仅为
0.00135 倍弦长且偏转角为45°的沟槽阵列可以使翼型稳定工作范围拓宽28.57%。流场细节表明：在沟槽内小尺度涡流的积聚效应以及沟槽上方展向迁移流动的共同作用下，翼型汇聚线附近形成了一对强度相同方向相反的诱导涡，这加强了附面层与主流的掺混，使附面层获得足够的能量用于抵抗大攻角工况下的逆压力梯度，有效延缓了翼型失速。Abstract:Taking the NACA0012 airfoil as the research object, the control rules and physical mechanisms of bio-inspired herringbone groove array on airfoil stall were explored through numerical simulations. The herringbone groove array was placed on the airfoil's upper surface near the trailing edge, and the effects of groove depth and deflection angle on the control effectiveness were investigated. The results showed that different designs of herringbone groove array can effectively broaden the stable operating range of the airfoil, and the implementation of herringbone groove array with a depth of only
0.00135 chord length and a deflection angle of 45° can increase the stable operating range by 28.57%. Detailed flow field analysis revealed that, due to the accumulation of small-scale vortices inside the grooves and the combined effect of the spanwise migration flow above the grooves, a pair of induced vortices with equal strength but opposite directions were formed near the airfoil's convergence lines. The induced vortices enhanced the mixing of the boundary layer with the mainstream flow, providing enough energy for the boundary layer to resist adverse pressure gradients under high angles of attack and effectively delaying airfoil stall.-
Key words:
- airfoil stall /
- flow control /
- herringbone groove array /
- vortex generator /
- additional losses
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图 4 布置人字形沟槽阵列的翼型网格划分
Figure 4. Mesh distribution of airfoil with herringbone groove array
图 5 原始翼型数值结果与实验结果的对比（Re=1.8×106）
Figure 5. Comparison of numerical results with experimental results for the prototype airfoil （Re=1.8×106）
图 6 沟槽深度对翼型升力和阻力特性的影响
Figure 6. Effects of groove depth on airfoil lift and drag characteristics
图 7 偏转角对翼型升力和阻力特性的影响
Figure 7. Effects of yaw angle on airfoil lift and drag characteristics
图 8 沟槽不同设计参数下翼型的总压损失云图和流线图（
$ \alpha = 16{\text{°}} $ ）Figure 8. Total pressure loss coefficient and streamlines of airfoil with different design grooves （
$ \alpha = 16{\text{°}} $ ）
图 9 人字形沟槽阵列内的三维流线（Case 3,
$ \alpha = 3{\text{°}} $ ）Figure 9. Three-dimensional flow within the herringbone groove array （Case 3,
$ \alpha = 3{\text{°}} $ ）
图 10 人字形沟槽阵列上方近壁面的三维流线（Case 3,
$ \alpha = 3{\text{°}} $ ）Figure 10. Three-dimensional flow near the upper surface of the herringbone groove array （Case 3,
$ \alpha = 3{\text{°}} $ ）
图 11 翼型不同截面处涡量x方向分量云图（Case 3,
$ \alpha = 3{\text{°}} $ ）Figure 11. x-directional components of vorticity at different sections of the airfoil （Case 3,
$ \alpha = 3{\text{°}} $ ）
图 12 翼型不同截面处速度x方向分量云图（Case 3,
$ \alpha = 3{\text{°}} $ ）Figure 12. x-directional components of velocity at different sections of the airfoil （Case 3,
$ \alpha = 3{\text{°}} $ ）
图 13 不同设计的人字形沟槽阵列在95%
$ c $ 截面处涡量场云图（$ \alpha = 3{\text{°}} $ ）Figure 13. Vorticity fields of herringbone groove array with different designs at the 95%
$ c $ plane （$ \alpha = 3{\text{°}} $ ）表 1 人字形沟槽阵列几何参数
Table 1. Geometrical parameters of herringbone groove array
参数 数值 长度 $ L $/$ c $ 0.2 宽度 $ W $/$ c $ 0.2 沟槽宽度 $ s $/$ c $ 0.01 
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表 2 人字形沟槽阵列的计算方案
Table 2. Computation schemes of herringbone groove array
方案 沟槽深度$ h $/$ c $ 沟槽偏转角$ \gamma $/（°） Case 1 0.000675 45 Case 2 0.001 45 Case 3 0.00135 45 Case 4 0.002 45 Case 5 0.0027 45 Case 6 0.00135 30 Case 7 0.00135 38 Case 8 0.00135 53 Case 9 0.00135 60
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表 3 不同方案的稳定工作范围拓宽量
Table 3. Extension of the stable working range for different schemes
方案 稳定工作范围拓宽量$ \Delta {\alpha ^*} $/% Case 1 10.71 Case 2 17.86 Case 3 28.57 Case 4 17.86 Case 5 14.29 Case 6 20 Case 7 25 Case 8 20 Case 9 10.71
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