Stereoscopic PIV measurements of leading edge separation vortices on a cranked arrow wing
Stereoscopic PIV measurements of leading edge separation vortices on a cranked arrow wing
复制标题
曲柄箭翼前缘分离涡的立体 PIV 测量
DOI：
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发表时间：
2004
期刊：
影响因子：
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通讯作者：
K. Rinoie
中科院分区：
文献类型：
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作者：
Shigeya Watanabe;H. Kato;D. Kwak;Masashi Shirotake;K. Rinoie
为了更好地了解背风流动现象，重点研究了迎角效应和雷诺数效应，给出了中心机身曲柄箭翼背风三分量速度的立体PIV测量结果。试验在低速风洞中进行，雷诺数范围为0.15×106~1.5×106，迎角为8°~20°。根据瞬时结果，推导出了湍流动能等统计特性。试验结果表明，随着迎角的增大，两个前缘分离涡与机身上的一个涡之间的相互作用变强，并合并成一个涡。在攻角效应方面，分离涡中心的涡量大小与动能呈正相关。雷诺数效应的结果表明，随着雷诺数的增加，二次涡结构变小，两个主要分离涡向外移动，内侧翼面边界层过渡导致涡的核心直径变大，涡量变小。一般来说，这些雷诺数效应与攻角减小的效应相似。
Three-component velocity measurement results via stereoscopic PIV for leeward flow of a cranked arrow wing with a centre body are presented in order to understand leeward flow phenomena, emphasizing angle-of-attack effects and Reynolds number effects. The tests are conducted in a low-speed wind tunnel with the Reynolds number range from 0.15 × 106 to 1.5 × 106 at angles of attack of 8° to 20°. Based on instantaneous results, statistical properties such as turbulence kinetic energy are derived. The test results indicate that with increase in angle of attack, interaction between two leading edge separation vortices and a vortex on the body becomes strong, merging into a single vortex. In results on angle of attack effects, vorticity magnitude and kinetic energy have a positive correlation in the cores of the separation vortices. Results of Reynolds number effects show that with increasing Reynolds number, the secondary vortex structure becomes small with the two primary separation vortices moving outward, and the core diameter and vorticity of the vortices become larger and smaller, respectively, due to boundary layer transition on the inboard wing. In general, these Reynolds number effects are similar to the effects of decrease in angle of attack.