Application of a smart material structure in the study of aerodynamic characteristics of a morphing wing
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摘要: 为验证所提出的智能材料结构在柔性变后缘机翼气动特性研究中应用的可行性，在跨声速风洞中运用模型变形视频测量技术测量了机翼后缘的偏转变形量，并记录了偏转变形的动态过程。同时测量了上翼面的压力分布。实验马赫数0.4~0.8，模型迎角0°~6°。分析了来流条件对结构变形能力的影响。结果表明：跨声速条件下，智能材料结构在气动载荷作用下能够驱动机翼后缘偏转变形。驱动力一定时，变形能力受到马赫数和迎角等因素影响。马赫数增加会减弱智能材料结构的变形能力，导致变形速度减小，后缘偏转角降低。迎角的影响较为复杂，且与马赫数的影响相互耦合，马赫数越高迎角的影响越强。最后，通过对后缘压力分布形态的分析得出，变形后后缘是否发生流动分离是影响智能材料结构变形能力的关键因素。Abstract: In order to verify the feasibility and deformation capability of the intelligent material structure in the study on aerodynamic characteristics of the flexible variable trailing edge wing, the videogrammetric model deformation technique is used to measure the deflection of the trailing edge in the transonic wind tunnel, and the dynamic process of deflection is recorded. The pressure distribution on the upper wing surface is also measured. The Mach number is between 0.4 and 0.8, and the model's angle of attack is between 0° and 6°. The influence of flow condition on the structure deformation is analyzed. The test result shows that the flexible structure of the model can bear the aerodynamic load of the transonic flow and achieve the deflection. When the driving force is constant, the deformation is influenced by the Mach number and the angle of attack. The increase of Mach number weakens the deformation ability of the intelligent structure, which leads to the decrease of the deformation speed and the decrease of the trailing edge deflection angle. The influence of the angle of attack is more complex, and couples with the influence of the Mach number. The higher the Mach number, the stronger the influence of attack angle. Finally, through the analysis of the pressure distribution, it is concluded that the flow separation is the key factor to influence the deformation capacity of the intelligent material structure.
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图 2 连续可变弯度后缘襟翼试验照片
Figure 2. The test photo of variable camber continuous trailing edge flap
图 12 Ma=0.4后缘偏转角分布测量结果
Figure 12. Measurement results of trailing edge deflection angle when Ma=0.4
图 13 Ma=0.5后缘偏转角分布测量结果
Figure 13. Measurement results of trailing edge deflection angle when Ma=0.5
图 14 Ma=0.6后缘偏转角分布测量结果
Figure 14. Measurement results of trailing edge deflection angle when Ma=0.6
图 15 Ma=0.7后缘偏转角分布测量结果
Figure 15. Measurement results of trailing edge deflection angle when Ma=0.7
图 16 Ma=0.8后缘偏转角分布测量结果
Figure 16. Measurement results of trailing edge deflection angle when Ma=0.8
图 17 α=2°后缘偏转角分布测量结果
Figure 17. The measurement results of the angle distribution when α=2°
图 18 α=2°后缘偏转角速度测量结果
Figure 18. The measurement results of the angular velocity of deflection when α=2°
图 19 最大后缘偏转角测量结果
Figure 19. Measurement results of maximum trailing edge deflection angle
图 20 Ma=0.5变形前后压力分布对比
Figure 20. Comparison of pressure distribution before and after deformation when Ma=0.5
图 21 Ma=0.7变形前后压力分布对比
Figure 21. Comparison of pressure distribution before and after deformation when Ma=0.7
表 1 试验状态表
Table 1. Test condition
流场参数 数值 Ma 0.4 0.5 0.6 0.7 0.8 AOA/(°) 0°、2°、4°、6° Re/106 1.27 1.54 1.81 2.11 2.32 Dynamic pressure/Pa 9891 14619 20143 26532 32258 
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