Mechanism and Ground Effect Analysis on Blowing Control of a Seamless Flap
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摘要: 基于Coanda效应的无缝襟翼吹气控制能大幅度提升机翼升力, 改善大型运输类飞机起降性能, 因此研究起降阶段地面效应对吹气控制的影响十分必要。通过数值模拟方法, 从流场变化的角度分析了无缝襟翼吹气控制机理, 以及有/无襟翼吹气时地面效应对翼型气动性能的影响。襟翼吹气使Coanda表面产生局部低压区, 形成指向Coanda表面的压力梯度, 进而引起射流上方的主流偏转和加速, 使整个翼面近壁区产生顺时针方向的速度增量; 翼面压力面的压力增大, 吸力面的吸力增强, 其中主翼上翼面吸力增强是翼型升力增加的主要来源。无吹气时, 地面效应使翼型上/下翼面附近的流速均降低, 上/下翼面的压力均有所提高, 整体上使翼型升力降低。有地面效应时的襟翼吹气增强了下翼面对来流的阻滞作用, 进一步提高了下翼面的压力; 襟翼吹气使上翼面气流加速, 可抵消地面效应引起的上翼面气流减速, 一定程度上减小了地面效应引起的上翼面吸力损失。Abstract: Blowing control of seamless flap based on Coanda effect can greatly increase the wing lift and improve the take-off and landing performance of transport aircrafts. Therefore, it is essential to investigate the influence of ground effect on the blowing control. In this paper, the blowing control mechanism of a seamless-flap airfoil, as well as the ground effect on aerodynamic performance with and without blowing, was analyzed by numerical simulation from the perspective of flow field variation. Flap blowing creates a local low pressure area near the Coanda surface, forming a pressure gradient pointing to the Coanda surface, and then causes the mainstream above the jet to deflect and accelerate, resulting in a clockwise velocity increment in the entire near-wall area of the wing surface. The velocity increment near the wing surface increases the pressure of the lower surface and strengthens the suction of the upper strengthens. The increase of suction on the upper surface of the main wing is the main source of airfoil lift increment. Without blowing, the ground effect reduces the flow velocity near both upper and lower airfoil surfaces, increases the pressure around the airfoil, and reduces the airfoil lift as a whole. The flap blowing with ground effect enhances the blocking effect of the lower surface on the incoming flow, and further increases the pressure of the lower surface. The flap blowing accelerates the airflow on the upper wing surface, which can compensate the velocity reduction and the suction loss of the upper surface caused by the ground effect.
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Key words:
- blowing control /
- seamless flap /
- ground effect /
- numerical simulation /
- Coanda effect
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图 4 0°迎角时计算区域和局部网格
Figure 4. Computational domain and local mesh of the airfoil at α=0°
图 8 吹气控制前后壁面压力系数和局部流线
Figure 8. Pressure coefficients and local streamlines before and after blowing control
图 10 吹气引起的平均流场净增量
Figure 10. Net increment of average flow field caused by blowing at Cμ=0.01 and Cμ=0.08
图 12 α=0°和8°，h/c=0.2引起的速度、压力、密度的净增量
Figure 12. Net increment of velocity, pressure and density for α=0° and 8°at h/c=0.2
图 13 α=0°，h/c=2.0相对于h/c=∞时引起的速度、压力净增量
Figure 13. Net increment of velocity and pressure caused by h/c=2.0 relative to h/c=∞
图 15 吹气加地效时壁面压力系数
Figure 15. Wall pressure coefficients with air blowing and ground effect
图 16 吹气加地面效应时的速度净增量
Figure 16. Net increment of velocity with air blowing and ground effect
表 1 3种网格的参数
Table 1. Parameters of the three grids
case the height of the first grid circumferential grids the total number of grids CL 1 0.000 11c
(y+ < 4)580 42 348 3.558 6 2 0.000 055c
(y+ < 2)785 54 959 3.582 3 3 0.000 025c
(y+ < 1)990 69 412 3.589 5 
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表 2 吹气后翼面各部分对增升量的贡献率
Table 2. Lift increment of each part of the airfoil surface after blowing
part Cμ=0.01 Cμ=0.08 upper surface of the flap 6.0% 15.7% the entire lower surface 12.3% 9.5% upper surface of main wing 81.7% 74.8%
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表 3 吹气前后不同离地高度的计算结果
Table 3. Calculation results at different heights before and after blowing control
case without blowing blowing(Cμ=0.028) dominant frequency of the flow/Hz CL CD CL CD α=0°，h/c=0.2 68.03 1.703 0.131 2.586 0.026 α=0°，h/c=2.0 74.63 1.765 0.164 3.325 0.034 α=0°，h/c= ∞ 78.13 1.847 0.181 3.621 0.048 α=8°，h/c=0.2 59.17 2.086 0.129 2.586 0.045 α=8°，h/c=2.0 67.11 2.357 0.178 3.249 0.060 α=8°，h/c= ∞ 69.93 2.507 0.201 3.560 0.077
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