多种翼梢装置的气动特性研究

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• 英文论文题名：Research on Aerodynamic Characteristics of Several Wingtip Devices
• 论文作者：刘毅 ; 赵晓霞
• 英文论文作者：Liu Yi ; Zhao Xiaoxia ; Research and Development Center ; AVIC Aircraft CO.LTD.
• 年：2016
• 作者机构：中航飞机股份有限公司研发中心;
• 论文关键词：翼梢小翼 ; 翼尖涡 ; 诱导阻力 ; 流场特性
• 英文论文关键词：winglet ; wingtip vortex ; induced drag ; flowfield characteristics
• 会议召开时间：2016-10-31
• 会议录名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛文集（下册）
• 英文会议录名称：Discovery,Innovation and Communication——Proceedings of 7th CSAA Science and Technology Youth Forum
• 语种：中文
• 分类号：V224
• 学会代码：ZGHU
• 会议名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛
• 会议地点：中国广东中山
• 主办单位：中国航空学会
• 学会名称：中国航空学会
• 页数：4
• 文件大小：1175k
• 原文格式：O
• 会议级别：全国

摘要

采用数值计算方法分析了4种翼梢装置(分别为:上反式、下反式、上下式、三小翼)的气动力和流场特性.研究了其减阻的机理,并与翼尖延伸方案进行了对比。四种翼梢装置均使飞机诱导阻力降低且减阻量大致相当,相对翼尖延伸方案减阻量提升了约40%。从翼根弯矩的增加量来看各方案的增加量在3.5%~5.5%之间,其中上反式小翼弯矩增加量偏大,三小翼方案翼根弯矩增量最小。从流场特性可见上反式、下反式小翼使机翼尾流中出现两个同向旋转的涡流核心:上下式、三小翼式翼梢装置则分别有3个、4个涡流核心。各翼梢小翼方案均使尾流中的横向速度分量显著降低。而翼尖延伸方案尾流中的旋涡流动降低不明显,导致其减阻效率低于翼梢装置.
Four types of wingtip devices(upper winglet,lower winglet,upper/lower winglets,triple winglets) are studied by numerical simulation to get their aerodynamic force and flow field characteristics.The mechanism of their drag reduction effect is investigated and compared with wingtip extension.Four types of wingtip devices reduce the induced drag of the aircraft by similar quantity,which is about 40%higher than wingtip extension.The wing root bending moment of the plans varies between 3.5%to5.5%.The upper winglet generates the largest wing root bending moment while the triple winglets generate the lest.Two vortex cores are generated by the upper and lower winglet behind the wing which rotate at the same direction.Three and four vortex cores are created by the upper/lower winglets and triple winglets respectively.The cross flow velocity of the winglet plans is significantly reduced while the wingtip extension does not reduce it much,which is the causal factor of its inferior drag reduction efficiency.

引文

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