Numerical study of the effect of trailing edge bluntness on highly turbulent hydrofoil flow
Numerical study of the effect of trailing edge bluntness on highly turbulent hydrofoil flow
复制标题
后缘钝度对高湍流水翼流影响的数值研究
DOI：
10.21914/anziamj.v47i0.1077
复制
发表时间：
2007
期刊：
影响因子：
0.9
通讯作者：
J. Tu
中科院分区：
文献类型：
--
作者：
T. Do;L. Chen;J. Tu
由于相关的复杂和不利现象，控制表面上的湍流尾缘流动一直是许多设计师和研究人员感兴趣的问题。在本研究中，对二维NACA0015翼型进行了尾缘修改，沿弦轴在不同位置垂直“切割”，从而改变了基于尾缘高度的雷诺数，同时保持基于弦长的雷诺数固定为349万。数值计算结果表明，对于尾缘为钝的截面，涡脱落开始时的钝度参数与已发表的数据吻合较好。参数化研究表明，增大尾缘高度会降低旋涡脱落的频率。尾迹长度随尾缘雷诺数的增加的变化趋势与经过圆柱的流动相似。这个钝截面的斯特劳哈尔数约为0.09。
Turbulent trailing edge flow over control surfaces continues to be of interest to many designers and researchers alike due to the associated complex and adverse phenomena. In this study a two dimensional NACA0015 airfoil was modified at the trailing edge by vertically `cutting' at various locations along the chord axis thereby changing the Reynolds number based on the trailing edge height, while keeping the chord-length based Reynolds number fixed at 3.49 million. The numerical results show the bluntness parameter at onset of vortex shedding agree well with published data for sections having a blunt trailing edge. A parametric study suggests that increasing the trailing edge height tends to reduce the frequency of vortex shedding. Also, the variational trend of wake formation lengths with increasing trailing edge Reynolds number resembles that of flow past a circular cylinder. The Strouhal number for this blunt section is approximately 0.09.