Measurement of Unsteady Aerodynamic Characteristics of a Heaving Wing in a Low Reynolds Number Flow
Measurement of Unsteady Aerodynamic Characteristics of a Heaving Wing in a Low Reynolds Number Flow
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DOI：
10.2322/tjsass.64.147
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发表时间：
2021
影响因子：
1.1
通讯作者：
M. Okamoto;Shota Fukatsu;D. Sasaki
中科院分区：
文献类型：
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作者：
M. Okamoto;Shota Fukatsu;D. Sasaki
本研究的目的是利用风洞确定在均匀流动中作用于起伏机翼的二维非定常气动力和力矩。然而，由于测量装置的振荡和机翼模型的大惯性力，使作用在升沉机翼上的气动力难以测量。在本研究中，开发了一种新型风洞试验，命名为“起伏风洞”。在这里，当风洞随着起伏运动振荡时，机翼模型保持静止。该实验方法的优点是测量结果不受作用在振荡翼模型上的大惯性力的影响。因此，机翼模型可以与稳态实验一样使用。利用研制的升沉风洞试验，测量了升沉翼型的法向力、推力和俯仰力矩系数。通过流动可视化和压力测量，我们发现法向力系数在达到最大值后迅速下降是由于前缘涡的巨大增长。
The objective of this study is to determine the two-dimensional unsteady aerodynamic forces and moment acting on a heaving wing in a uniform flow using a wind tunnel. However, it is difficult to measure the aerodynamic forces acting on the heaving wing due to measuring device oscillation and the large inertial force of the wing model. In this study, a new type of wind tunnel test, named ‘‘heaving wind tunnel,’’ was developed. Here, the wing model remains stationary as the wind tunnel oscillates with a heaving motion. The advantage of this experimental method is that the measurement results are unaffected by the large inertial force acting on the oscillating wing model. Therefore, the wing model can be used in the same way as in steady state experiments. The normal force, thrust and pitching moment coefficients of a heaving airfoil were measured using the heaving wind tunnel test developed in this study. Through flow visualizations and pressure measurements, we found that the rapid drop in normal force coefficient after it reached its maximum value was due to a large growing leading-edge vortex.