Low-Reynolds-Number Flowfield of Wing with Control Surface in Propeller Slipstream
Low-Reynolds-Number Flowfield of Wing with Control Surface in Propeller Slipstream
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DOI：
10.2514/1.c035880
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发表时间：
2021-03-01
影响因子：
2.2
通讯作者：
Nagai, Hiroki
中科院分区：
文献类型：
--
作者：
Ikami, Tsubasa;Fujita, Koji;Nagai, Hiroki
在NACA 0012翼型操纵面上进行了低雷诺数条件下螺旋桨滑流影响的实验研究。为了研究螺旋桨滑流对机翼表面的影响，在弦基雷诺数为3.0×10(4)的情况下，用温敏涂料显示了机翼表面的流场。在安装螺旋桨的情况下，由于螺旋桨滑流抑制了层流分离气泡，操纵面性能得到了改善。最后，建议在低雷诺数飞行条件下，螺旋桨应安装在操纵面前面，以获得螺旋桨滑流的影响。
An experimental study is conducted on a NACA 0012 airfoil with a control surface to investigate the influence of a propeller slipstream under a low-Reynolds-number condition. To investigate the influence of the propeller slipstream on a wing surface, the flowfield on the wing surface is visualized using a temperature-sensitive paint when the chord-based Reynolds number is equal to 3.0 x 10(4). The control surface performance improves in the installed-propeller condition because the propeller slipstream suppresses the laminar separation bubble. Finally, we suggest that the propeller should be installed ahead of the control surface to benefit from the effect of the propeller slipstream under the low-Reynolds-number flight condition.