Effect of 90 Degree Flap on the Aerodynamics of a Two-Element Airfoil
Effect of 90 Degree Flap on the Aerodynamics of a Two-Element Airfoil
复制标题
90 度襟翼对二元翼型空气动力学的影响
DOI：
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发表时间：
1989
期刊：
影响因子：
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通讯作者：
R. Largman
中科院分区：
文献类型：
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作者：
J. Katz;R. Largman
对带90 °后缘襟翼的二元翼型的气动性能进行了实验研究。5 °弦长的长襟翼在很大的迎角范围内显著地增加了基线翼型的升力。有襟翼机翼的最大升力系数增大，而升阻比减小。
The aerodynamic performance of a two-element airfoil with a 90-deg trailing edge flap was experimentally investigated. The 5 percent-chord long flap, significantly increased the lift of the baseline airfoil, throughout a wide range of angles of attack. The maximum lift coefficient of the flapped wing increased too, whereas the lift/drag ratio decreased.