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Experimental study on the vortex structure and path instability of freely falling annular disks
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作者 bi dianfang WEI YingJie +1 位作者 WANG Cong XU Hao 《Science China(Technological Sciences)》 SCIE EI CAS CSCD 2018年第6期853-866,共14页
Bodies freely falling in steady water or air are common scenes encountered in various scientific and engineering fields, including the flapping flight of birds and the reentry of a space shuttle. In this work, the fre... Bodies freely falling in steady water or air are common scenes encountered in various scientific and engineering fields, including the flapping flight of birds and the reentry of a space shuttle. In this work, the freely falling annular thin disks with small dimensionless moments of inertia f and Reynolds number Re are investigated experimentally in a water tank. We use stereo- scopic vision to record the position and orientation of the disks. The flow structure behind the disks is studied by applying fluorescent dye visualization and PIV method. Varying the geometry dimensionless parameter (the inner to outer diameter ratio η and I*) of the disks reveals two new falling patterns. When ηcritl=0.6〈η〈ηcrit2=0.8, the disks show a random lateral vibration while falling. For high ηcrit2〉0.8, the circular vortex loops shed frequently from the disk, which causes a lengthways vibration superimposed onto straight vertical motion. We also observe another two falling patterns reported previously: hula-hoop and helical motion. By comparing the wake structure of the two motions, we find that the vortex layer twists more violently in the hula-hoop motion, which is the reason for the different trajectory between them. Further research on flow field reveals that the torque on the disk that causes the vibration is due to the formation, elongation and shedding of the vortex. 展开更多
关键词 flow-structure interactions vortex shedding path instability
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基于射流飞控技术的环量控制阶段数值研究
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作者 王睿雯 毕殿方 黄旭东 《清华大学学报(自然科学版)》 EI CAS CSCD 北大核心 2024年第2期346-357,共12页
环量控制技术通过调节射流喷气量实现翼型气动性能的提升,在Coanda效应作用下,翼型环量会发生改变,且尾缘后流场出现分离。目前环量控制的分离位置与射流位置、射流高度及射流强度的关系尚不明确。该文主要研究了Coanda效应对流场分布... 环量控制技术通过调节射流喷气量实现翼型气动性能的提升,在Coanda效应作用下,翼型环量会发生改变,且尾缘后流场出现分离。目前环量控制的分离位置与射流位置、射流高度及射流强度的关系尚不明确。该文主要研究了Coanda效应对流场分布及升阻力特性的影响,并对环量控制的不同控制阶段进行了分析。首先,对NACA0012标准翼型进行尾缘修型,改变尾缘曲率和喷口高度等参数,验证环量控制的有效性;其次,在考虑攻角、动量系数、射流速度3个关键参数的情况下,引入Coanda偏转角,揭示了环量控制的Coanda效应的触发及抑制机理;最后,对NACA0012修型翼型和CC-E0020EJ环量控制翼型提出了分离预测思路。针对环量控制技术中2个控制阶段,通过推阻分解法对升力、阻力进行解构,解释了尾缘后流场分离与再附的超临界现象,提出了分离区域的分析方法。结果表明:Coanda偏转角可以作为动量系数与升力系数的物理判据,翼型下表面的压力损失导致超环量阶段的射流效率降低。 展开更多
关键词 环量控制 Coanda效应 失速特性 射流飞行控制 气动增升
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