一种下单翼飞机近距耦合导流片的设计与研究  

Design and Research on the Close Coupled Guiding Vanes for a Low Wing Aircraft

作　　者：梅源 刘毅 赵新新 王磊平 MEI Yuan;LIU Yi;ZHAO Xinxin;WANG Leiping(School of Automobile and Aviation Engineering,Wuhu Institute of Technology,Wuhu Anhui 241000,China;Department of General Design,CETC Wuhu General Aviation Industrial Technology Research Institute Co.,Ltd.,Wuhu Anhui 241000,China)

机构地区：[1]芜湖职业技术学院汽车与航空学院,安徽芜湖241006 [2]中电科芜湖通用航空产业技术研究院有限公司,安徽芜湖241000

出　　处：《佳木斯大学学报（自然科学版）》2024年第4期78-82,共5页Journal of Jiamusi University：Natural Science Edition

基　　金：安徽省教育厅科学研究项目(2022AH052190):通用飞机翼身气动特性关键技术研究;安徽省质量工程项目(2022jnds062):省级技能大师工作室;芜湖职业技术学院科技创新团队:Wzykytd202202,Wzykytd202203;芜湖市交通动力装备工程技术研究中心:Sgcjsyjzx09;安徽省教育厅科学研究项目(KJ2020ZD72)。

摘　　要：某下单翼通用飞机在大迎角时出现上翼面翼根气流分离,导致飞机最大升力系数降低。在机翼翼根前方的机身上加装小展弦比导流片,通过尾涡为分离区注入的高能气流改善了后方机翼的流场,后方机翼则通过绕流流场诱导导流片尾涡贴近机翼翼面,二者形成了有利耦合。导流片参数影响研究表明导流片与机翼根部翼型相对重叠量约0.023时取得了较好的增升效果,最大升力系数增加量可达0.32。若导流片位置进一步远离机翼则不能与机翼流场耦合,重叠量加大则导流片受机翼干扰自身涡强不足。导流片较优的安装角应保证在机翼大迎角时导流片法向力系数足够大,且失速迎角大于机翼失速迎角。A low wing general aircraft suffered from flow separation at the root area of the upper wing at large angles of attack,which reduced the maximum lift coefficient.By installing a pair of low-aspect-ratio guiding vanes on the fuselage ahead of the wing root,high energy air created by their wake flow is injected into the separation area,ameliorating the flow field.Meanwhile the afterwards wing induces the wake flow of the guiding vanes to be close to the wing surface,and the beneficial coupling is formed.The parametric study shows that lift enhancement effect is higher when the relative overlap between the vane and the wing root airfoil is 0.023,and the maximum lift coefficient is increased by 0.32.When the vanes move further from the wing,the flowfield coupling disappears.On the contrary when the overlap is higher,the vortex strength of the vanes is not enough due to the interference of the wing.The optimum vane incident angle is that the normal force coefficient of the vane being large enough at large angle of attack of the wing while its stall angle is higher than the wing.

关 键 词：导流片 下单翼 气流分离 涡流 最大升力系数 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]