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首页> 外文会议>Third Asia-Pacific International Symposium on Aerospace Technology >Airfoil Stall Suppression by Use of Smart Structure Sensor Actuators for NACA 631-012
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Airfoil Stall Suppression by Use of Smart Structure Sensor Actuators for NACA 631-012

机译：使用适用于NACA 631-012的智能结构传感器执行器来抑制机翼失速

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摘要

The authors have been conducting an investigation to suppress airfoil stall by controlling the laminar separation bubble formed on the airfoil. One of the authors got an idea that the bubble burst could be suppressed by enhancing the turbulent vortical structures in the separated shear layer by use of a thin plate placed inside the bubble. Wind tunnel tests were conducted for NACA 0012 and NACA 631-012 airfoil and concluded that this plate is an effective device to control the airfoil stall. Further investigations have been done to develop a system that automatically determines the optimum configuration of the plate. The developed system is the one consisted of smart structure sensor actuators, surface pressure sensor and feedback control mechanism. The wind tunnel measurements to confirm the benefit of this system was conducted for NACA 631-012 airfoil. In this paper, detailed results of this investigation are summarized.
机译：作者一直在进行研究，通过控制在机翼上形成的层状分离气泡来抑制机翼失速。一位作者想到了可以通过使用放置在气泡内部的薄板增强分离的剪切层中湍流涡旋结构来抑制气泡破裂的方法。对NACA 0012和NACA 631-012机翼进行了风洞测试，得出的结论是该板是控制机翼失速的有效装置。已经进行了进一步的研究以开发一种系统，该系统可自动确定板的最佳配置。开发的系统是由智能结构传感器执行器，表面压力传感器和反馈控制机制组成的系统。为确认该系统的优势，对NACA 631-012机翼进行了风洞测量。本文总结了这项调查的详细结果。

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