Home The Proceedings of the 2021 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2021), Volume 1 Conference paper Low-Speed Wind Tunnel Testing of a Passive Camber Morphing Airfoil Using a 3D-Printed Compliant Mechanism
Home The Proceedings of the 2021 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2021), Volume 1 Conference paper Low-Speed Wind Tunnel Testing of a Passive Camber Morphing Airfoil Using a 3D-Printed Compliant Mechanism
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首页 2021 年亚太航空航天技术国际研讨会 (APISAT 2021) 第 1 卷会议论文 使用 3D 打印顺应机构对被动弯度变形翼型进行低速风洞测试
DOI：
10.1007/978-981-19-2689-1_78
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发表时间：
2022
期刊：
影响因子：
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通讯作者：
Tomohiro Yokozeki & Kenichi Rinoie
中科院分区：
文献类型：
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作者：
Shoko Kai;Shogo Takazawa;Shuji Ochi;Taro Imamura;Tomohiro Yokozeki & Kenichi Rinoie
对被动后缘变形翼型模型进行了气动特性的实验研究。虽然大多数变形翼型使用致动器控制，但被动变形翼型由于翼型表面的静压和模型柔性之间的平衡而变形。在我们先前的研究中，所设计的变形翼型模型有一个有趣的特点。随着升力的增加，翼型的弯度增加，从而获得更高的升力。同时，模型的内部结构复杂;因此，必须使用24%厚度的翼型（NACA 0024），并且难以保持模型制造精度。考虑到对飞机的适应性，有必要研究更薄翼型的气动性能，并制作更精确的模型。基于NACA 0012模型制作了一种新的被动变形翼型模型。简化了内部结构，实现了减薄和高模型制造精度。通过低速风洞实验测量了其变形和气动特性。观察到两个变形特征，（1）减小的有效迎角（AOA）和（2）增加的拱。随着攻角的增大，变形逐渐增大。与刚性翼型相比，最大升力系数提高了13%。此外，在失速角下，被动翼型的升力系数比刚性翼型下降得更慢。
Experimental investigations into the aerodynamics of the passive trailing-edge morphing airfoil model are presented. While most morphing airfoils are controlled using actuators, the passive morphing airfoil deforms due to the balance between the airfoil surface’s static pressure and the model flexibility. In our previous study, the designed morphing airfoil model had an interesting characteristic. As lift force increased, the camber of the airfoil increased and a higher lift was achieved. Meanwhile, the internal structure of the model was complex; thus, 24% thickness airfoil (NACA0024) had to be used, and maintaining a model-manufacturing accuracy was difficult. Considering adaptation to aircraft, it is necessary to study thinner airfoils in terms of aerodynamic performance and to manufacture models more accurately. Therefore, a new passive morphing airfoil model was manufactured based on NACA0012. The internal structure was simplified to realize thickness reduction and high model-manufacturing accuracy. The deformation and aerodynamic characteristics were measured through low-speed wind tunnel experiments. Two deformation characteristics, (1) decreasing of the effective angle-of-attack (AOA) and (2) increasing of the camber, were observed. In addition, the deformation gradually increased as the AOA increased. The maximum lift coefficient increased by 13% compared with the rigid airfoil. Further, the lift coefficient of the passive airfoil tailed off slower than the rigid airfoil at a stall angle.