Wake Structures Behind Plunging Airfoils: A Comparison of Numerical and Experimental Results
Wake Structures Behind Plunging Airfoils: A Comparison of Numerical and Experimental Results
复制标题
俯冲翼型背后的尾流结构：数值与实验结果的比较
DOI：
10.2514/6.1996-78
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发表时间：
1996
期刊：
影响因子：
2.5
通讯作者：
K. D. Jones
中科院分区：
文献类型：
--
作者：
M. Platzer;C. M. Dohring;K. D. Jones
比较数值和实验产生的尾迹结构后，翼型进行快速，振荡暴跌运动。使用非定常面板代码进行数值模拟。本文用拉格朗日网格法，用离散点涡近似非定常尾迹，计算了任意运动翼型的无粘不可压流。数值计算的结果使用交互式图形动画界面进行可视化。实验数据来自低速水洞。双色染料注入被用来显示非定常尾流结构，速度数据是使用激光多普勒测速仪。涡位置的比较符合线性理论的低振幅运动。对于大振幅、高频率运动，结果偏离线性理论，但两种方法的尾流彼此比较良好，包括针对高振幅、高频率运动获得的高度非线性、非对称尾流。两种方法的计算速度曲线和积分推力系数符合得很好。
Comparisons are made between numerically and experimentally produced wake structures behind airfoils undergoing rapid, oscillatory plunging motions. Numerical simulations are performed using an unsteady panel code. Inviscid, incompressible ows about arbitrary moving airfoils are computed with the unsteady wake approximated by discrete point vortices, tracked using a Lagrangian mesh scheme. Numerically computed results are visualized using an interactive, graphical-animation interface. Experimental data are obtained from a low-speed water tunnel. Two-color dye injection is used to visualize unsteady wake structures, and velocity data are acquired using laser doppler velocimetry. Comparisons of vortex location agree well with linear theory for low amplitude motions. For large amplitude, high frequency motions, results diverge from linear theory, but wakes from the two approaches compare well with each other, including highly non-linear, non-symmetric wakes obtained for high amplitude, high frequency motions. Computed velocity pro les and integrated thrust coe cients for both approaches agree well.