Separation and Reattachment Points of a NACA0012 Airfoil in a Periodic Flow under Low Reynolds Number

Hirohisa YAMANISHI; Yohsuke TANAKA; Shigeru MURATA

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Separation and Reattachment Points of a NACA0012 Airfoil in a Periodic Flow under Low Reynolds Number

机译：低雷诺数下NACA0012翼型在周期性流动中的分离和重新附着点

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We observed two-dimensional vorticity fields on a NACA0012 airfoil in a periodic flow modeled as a gust flow with a sinusoidal velocity profile in the streamwise direction. Experiments were conducted by using particle image velocimetry in a water tunnel under conditions of Re =3.0 × 103 and 15~(°) angle of attack. We found that phase-turbulence intensity fields illustrate the separation and reattachment points more quantitatively than do phase-averaged vorticity fields.

机译：我们在NACA0012机翼上的二维涡流场中观察到了周期性流动，该周期性流动被建模为阵风流动，在气流方向上具有正弦速度分布。在Re ＝ 3.0×103和15°（°）迎角的条件下，在水隧道中使用粒子图像测速法进行了实验。我们发现相湍流强度场比相均场涡度场更定量地说明了分离点和重新附着点。

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《Advanced Experimental Mechanics》 |2016年第2期|共6页
作者
Hirohisa YAMANISHI; Yohsuke TANAKA; Shigeru MURATA;
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中图分类力学;
关键词
Low Reynolds NumberNACA0012Periodic FlowSeparation and Reattachment Points;

机译：低雷诺数NACA0012周期性流分离和重新连接点;

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专利

1. Localization of Flow Separation and Transition Over a Pitching NACA0012 Airfoil at Transitional Reynolds Numbers Using Hot-Films [J] . Poels Allison, Rudmin Daniel, Benaissa Azemi, Journal of Fluids Engineering: Transactions of the ASME . 2015,第12期

机译：使用热膜在过渡雷诺数下的俯仰NACA0012翼型流分离和过渡的局部化
2. Low Reynolds unsteady flow simulation around NACA0012 airfoil with active flow control [J] . Akbarzadeh P., Lehdarboni A. Askari, Derazgisoo S. M. Meccanica: Journal of the Italian Association of Theoretical and Applied Mechanics . 2018,第14期

机译：NACA0012翼型的低雷诺不稳定流模拟，具有主动流量控制
3. Strong transient effects of the flow around a harmonically plunging NACA0012 airfoil at low Reynolds numbers [J] . Yucel S. Banu, Sahin Mehmet, Unal M. Fevzi Theoretical and Computational Fluid Dynamics . 2015,第5a6期

机译：在低雷诺数下，谐波骤降的NACA0012机翼周围的流动具有强烈的瞬态效应
4. Large-Eddy Simulations of Flow Control Effects of a DBD Plasma Actuator at Various Burst Frequencies on a Dynamic Flowfield around a Pitching NACA0012 Airfoil at Reynolds Number of 256,000 [C] . Hiroaki Fukumoto, Hikaru Aono, Taku Xonomura, AIAA aerospace sciences meeting;AIAA SciTech forum . 2018

机译：雷诺数为256,000的俯仰NACA0012翼型周围动态流场上不同爆破频率下DBD等离子执行器流量控制效果的大涡模拟。
5. Localisation of flow separation and transition over a pitching NACA0012 airfoil at transitional Reynolds number. [D] . Rudmin, Daniel. 2013

机译：流分离和过渡在过渡雷诺数的俯仰NACA0012机翼上的定位。
6. Boundary Layer Separation and Reattachment Detection on Airfoils by Thermal Flow Sensors [O] . Hannes Sturm, Gerrit Dumstorff, Peter Busche, 2012

机译：热流传感器对机翼的边界层分离和重新附着进行检测
7. Boundary Layer Separation and Reattachment Detection on Airfoils by Thermal Flow Sensors [O] . Peter Busche, Dieter Westermann, Walter Lang, 2012

机译：基于热流传感器的翼型边界层分离与再附着检测

Separation and Reattachment Points of a NACA0012 Airfoil in a Periodic Flow under Low Reynolds Number

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