The effect of corrugated skins on aerodynamic performance
The effect of corrugated skins on aerodynamic performance
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波纹蒙皮对气动性能的影响
DOI：
10.1177/1045389x14521874
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发表时间：
2014
影响因子：
2.7
通讯作者：
M. Friswell
中科院分区：
文献类型：
--
作者：
Yuying Xia;O. Bilgen;M. Friswell
波纹蒙皮提供了一个很好的解决方案，变形机翼，由于其高度各向异性的行为。如果低刚度翼面在弦向方向上对齐，则翼型形状变化是可能的。与传统的翼型光滑蒙皮相比，波纹蒙皮影响机翼的局部和整体空气动力学。本研究的目的是研究波纹蒙皮对翼型整体空气动力学的影响，特别是升力和阻力特性。首先，在不同的雷诺数下，在风洞中和通过计算流体动力学对具有光滑轮廓的NACA 0012翼型进行空气动力学分析，并与文献中的数据进行比较。考虑了不同攻角（-10 ° ~ 10°）下的升力和阻力系数。其次，两个不同尺寸的波纹型线的NACA 0012翼型进行了实验研究和数值模拟。相对于具有光滑蒙皮的标准NACA 0012翼型，分析和量化了翼型尺寸和雷诺数的影响。初步的数值计算结果验证了实验数据。
Corrugated skins provide a good solution to morphing wings due to their highly anisotropic behavior. If the low stiffness corrugation plane is aligned in the chordwise direction, the airfoil shape change is possible. In contrast to the traditional smooth skin of an airfoil, a corrugated skin influences both the local and global aerodynamics of a wing. The aim of this study is to investigate the effect of a corrugated skin on the global aerodynamics of an airfoil, particularly lift and drag characteristics. First, the aerodynamic analysis of a NACA 0012 airfoil with a smooth profile is conducted, both in the wind tunnel and by computational fluid dynamics, at different Reynolds numbers and compared to the data in the literature. The lift and drag coefficients at different angles of attack, between −10° and 10°, are considered. Next, two NACA 0012 airfoils with different sized corrugated profiles are investigated both experimentally and by numerical simulation. The effects of corrugation size and Reynolds number are analyzed and quantified relatively to the standard NACA0012 airfoil with a smooth skin. Preliminary numerical results are validated using the experimental data.