摘要
为研究前缘突节对机翼流动特性的影响,基于NACA0018标准翼型,对具有光滑前缘的标准机翼和具有不同前缘突节的仿生机翼分别进行了流动特性分析。结果表明,标准机翼在20°攻角之后,升力系数急剧下降,失速特性表现明显。而仿生机翼的升力系数也会在某一特定角度出现不同程度的下降,但下降趋势比较缓和。在大攻角下,仿生机翼的升力系数普遍大于标准机翼,可以有效的改善机翼的失速特性。相比于单位长度内的突节个数,突节的幅值对气动特性的影响更为明显。根据特定攻角下机翼表面流线的分布规律可知,波峰的存在使得其所在区域的流动分离相较于光滑前缘机翼发生了推迟,致使仿生机翼在大攻角下依然具有较大升力系数。
Based on the NACA0018 standard airfoil,flow characteristics of both standard w ings w ith smooth leading edge and bionic w ings w ith different leading edge protuberances w ere analyzed to study the influences of leading edge protuberances. The results show that the lift coefficient of the standard w ing descended dramatically and the stall characteristic got obvious w hen the attack angle started to be higher than 20 degree. How ever,the lift coefficient of the bionic w ing decreased by different extents corresponding to some specific attack angles,and the decreasing trend w as slow er. At high attack angles,the lift coefficient of bionic w ings w as generally higher than that of standard w ings,w hich can improve effectively the stall characteristic of the w ing. The effects of the amplitude of protuberances on the aero dynamic characteristics w ere stronger than that of the number of protuberances under unit length. According to the distribution of surface streamline under a specific attack angle,the appearance of peaks prolonged the flow separation during the corresponding region compared to the w ings w ith smooth leading edge,resulting in the high lift coefficient of the bionic w ings even at high attack angles.
出处
《沈阳航空航天大学学报》
2017年第5期26-34,共9页
Journal of Shenyang Aerospace University
基金
国家自然科学基金(项目编号:11502149)
青年成长基金(项目编号:201427Y)
辽宁省教育厅系列项目(项目编号:L2015406)
关键词
驼背鲸鳍
前缘突节
仿生机翼
流动特性分析
失速特性
humpback whale fins
leading edge protuberance
bionic wings
flow characteristics analysis
stall characteristics
