Flow control and separation delay in morphing wing aircraft using traveling wave actuation
Flow control and separation delay in morphing wing aircraft using traveling wave actuation
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DOI：
10.1088/1361-665x/abd347
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发表时间：
2021-02-01
影响因子：
4.1
通讯作者：
Karami, M. Amin
中科院分区：
文献类型：
--
作者：
Olivett, Anthony;Corrao, Peter;Karami, M. Amin
这项研究研究了波传播的仿生学，这是水生生物的一种运动模式，用于变形飞机表面进行边界层控制的用例。从理论上讲，这种运动将动量注入机翼上表面的流动中，从而产生强制压力梯度，从而增加升力。建议该方法可用于控制流动分离并减少高迎角失速的可能性。这种机制的动机对于需要突然机动的飞机特别相关，特别是在大迎角下作为防止失速的安全措施。驱动机构由放置在机翼上表面下方的轻质压电陶瓷换能器组成。开环系统控制表面变形。二维傅里叶变换技术用于估计行波与驻波比，并使用欧拉伯努利梁理论进行了分析验证，并使用原型机翼进行了实验。使用一系列扫描激光测振测试来调整和验证传播波控制。定制的二维 NACA 0018 翼型在雷诺数约为 50 000 的低速风洞中测试了这一概念。行波以及升力和阻力的变化都将通过实验进行表征。
This study examines the biomimicry of wave propagation, a mode of locomotion in aquatic life for the use-case of morphing aircraft surfaces for boundary layer control. Such motion is theorized to inject momentum into the flow on the upper surface of airfoils, and as a consequence, creates a forcible pressure gradient thereby increasing lift. It is proposed that this method can be used to control flow separation and reduce the likelihood of stall at high angles of attack. The motivation for such a mechanism is especially relevant for aircraft requiring abrupt maneuvers, and especially at high angles of attack as a safety measure against stalling. The actuation mechanism consists of lightweight piezoelectric ceramic transducers placed beneath the upper surface of an airfoil. An open-loop system controls surface morphing. A two-dimensional Fourier Transform technique is used to estimate traveling to standing wave ratio, which is verified analytically using Euler Bernoulli beam theory, and experimentally using a prototype wing. Propagating wave control is tuned and verified using a series of scanning laser vibrometry tests. A custom two-dimensional NACA 0018 airfoil tests the concept in a low-speed wind tunnel with an approximate Reynolds Number of 50 000. Both traveling waves and the changes in lift and drag will be experimentally characterized.