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首页> 外文期刊>Journal of Aeronautics & Aerospace Engineering >CFD Analysis on MAV NACA 2412 Wing in High Lift Take-Off Configuration for Enhanced Lift Generation
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CFD Analysis on MAV NACA 2412 Wing in High Lift Take-Off Configuration for Enhanced Lift Generation

机译：高提升起飞配置下的MAV NACA 2412机翼的CFD分析，可增强生成力

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摘要

In a high lift take off configuration an MAV wing utilizes partially extended flaps and slats. Slats and Flaps are high lift devices installed on a wing for the purpose of augmenting Coefficient of Lift (C,). While Slats are installed on the leading edge of a wing the Flaps may be installed on the trailing edge or the leading edge of a wing. In this paper the effect of Slot size created by the Slats in percentage of wing chord ‘c’ and Double Slotted Flaps on C, fora MAV NACA 2412 has been studied using CFD analysis at 2*10° Reynolds Number. It is found that the maximum value of C, achieved is 67.134% higher than the plain NACA 2412 wing at 4 degrees angle of attack when slats are extended at 1.7 percent of wing chord ‘c’. The Stall angle of the MAV NACA 2412 wing in high lift take-off configuration was found to be 54 degrees whereas the plain NACA 2412 wing stalled at 20 degrees angle of attack.
机译：在高升力起飞配置中，MAV机翼使用部分延伸的襟翼和板条。板条和襟翼是安装在机翼上的高升力设备，目的是提高升力系数（C，）。当板条安装在机翼的前缘上时，襟翼可以安装在机翼的后缘或前缘上。在本文中，通过CFD分析在2 * 10°雷诺数下研究了MAV NACA 2412上由板条产生的缝隙尺寸对翼弦“ c”和双缝襟翼的百分比的影响。结果发现，当板条延伸至翼弦“ c”的1.7％时，在4度迎角下获得的C的最大值比普通NACA 2412机翼高67.134％。发现在高升力起飞配置下的MAV NACA 2412机翼的失速角为54度，而平原NACA 2412机翼在20度迎角失速时失速。

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