Near Field of the Tip Vortex Behind an Oscillating Rectangular Wing
Near Field of the Tip Vortex Behind an Oscillating Rectangular Wing
复制标题
振荡矩形机翼后面的尖端涡的近场
DOI：
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发表时间：
1998
期刊：
影响因子：
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通讯作者：
Youxin Zheng
中科院分区：
文献类型：
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作者：
B. Ramaprian;Youxin Zheng
在雷诺数为1：8 £ 10 5的低速风洞中进行。机翼的半展弦比为2。它以1Hz的频率和5度的振幅围绕10度的平均入射角振荡。瞬时LDV数据被用来获得信息的相位锁定的速度和涡度分量的分布，以及相位锁定的环流与发展中的涡旋。这些数据表明，在平均迎角下，近场振荡涡的平均轨迹与固定机翼非常接近。在所研究的条件下，涡流的长度和环流尺度以及所携带的最大环流都以显著的非准定常方式调制。然而，超过约0.7弦长，穿过大部分涡流内部的标准化环量分布在任何时候都表现出与固定机翼后面的涡流相同的普遍特性。
were performed in a low-speed wind tunnel at a Reynolds number of 1 :8 £ 10 5 . The wing had a semiaspect ratio of 2. It was oscillated at a frequency of 1 Hz and an amplitude of 5 deg around a mean incidence of 10 deg. The instantaneous LDV data were used to obtain information on the distribution of phase-locked velocity and vorticity components across the vortex, as well as the phase-locked circulation associated with the evolving vortex. The data indicate that the average trajectory of the oscillating vortex in the near e eld is very nearly the same as for a stationary wing at the mean incidence. The length and circulation scales, as well as the maximum circulation carried by the vortex e ow under the conditions studied, are modulated in a signie cantly nonquasisteady manner. Nevertheless, beyond about 0.7 chordlength, the normalized circulation distribution across most of the inner part of the vortex exhibits, at all times, the same universal behavior as the vortex behind a stationary wing.