带扰流片翼型的气动特性研究
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- 英文论文题名：Research on Aerodynamic Characteristics of an Airfoil Section with Spoiler Deflected
- 论文作者：江微 ; 袁志敏 ; 赵晓霞 ; 刘毅
- 英文论文作者：Jiang Wei ; Yuan Zhimin ; Zhao Xiaoxia ; Liu Yi ; 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：扰流片 ; 翼型 ; 涡流 ; 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：V211.41
- 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：5
- 文件大小：2665k
- 原文格式：O
- 会议级别：全国
摘要
采用求解RANS方程的方法研究了某型机绕流片偏转0°~75°范围内的翼型二维气动力和流场特性。扰流片的偏转破坏了原翼型的流线性,在扰流片之后产生了较大的涡流区:在扰流片偏转15°时涡流区尺寸较小,呈气泡形:偏转30°~60°范围内在翼型后缘附近有强涡流并伴随有较高的负压,扰流片后方的旋涡方向相反.强度较弱但范围较大;偏转75°时翼型后缘的涡流显著后移,强度变弱;在这两处涡流之外还存在诱导产生的其他次涡,涡流结构在不同迎角时相似。扰流片偏转60°范围内带来的升力系数降低量与偏转角近似为线性关系,阻力系数增加量正比于偏转角的二次方。偏转角75°时气动力的变化与小偏角范围内的规律出现偏离。
The two dimensional aerodynamic force and flow field of the airfoil section with spoiler deflected between 0°to 75° are studied by solving RANS equation.The spoiler breaks the streamlined shape of the airfoil,and large area of vortex flow region is created behind the spoiler.At deflection angle of 15° the vortex flow region is relatively small forming a bubble.At the deflection angle between 30° and 60°,strong vortex emerges near the end of the airfoil with high negative pressure,and another counterrotating vortex after the spoiler exist with weaker strength but larger area.Other induced secondary vortexes also exist.The overall vortex structure is similar at different angle of attacks.The lift coefficient drop due to the spoiler deflection is approximately proportional to the spoiler deflection angle within the range of 60°,while the drag increment is proportional to the angle to the power of 2.The aerodynamic force at spoiler angle of 75° diverges from the trend of the smaller angles.
The two dimensional aerodynamic force and flow field of the airfoil section with spoiler deflected between 0°to 75° are studied by solving RANS equation.The spoiler breaks the streamlined shape of the airfoil,and large area of vortex flow region is created behind the spoiler.At deflection angle of 15° the vortex flow region is relatively small forming a bubble.At the deflection angle between 30° and 60°,strong vortex emerges near the end of the airfoil with high negative pressure,and another counterrotating vortex after the spoiler exist with weaker strength but larger area.Other induced secondary vortexes also exist.The overall vortex structure is similar at different angle of attacks.The lift coefficient drop due to the spoiler deflection is approximately proportional to the spoiler deflection angle within the range of 60°,while the drag increment is proportional to the angle to the power of 2.The aerodynamic force at spoiler angle of 75° diverges from the trend of the smaller angles.
引文
[1]《飞机设计手册》总编委会.飞机设计手册(第6册):气动设计.北京:航空工业出版社,2002:104-107.
[2]McLachlan B G,Karamcheti K.An Experimental Study of Airfoil-Spoiler Aerodynamics.NASA Contractor Report177328,1985.
[3]Al-Bahi,A M,Ghazi M A.An experimental Investigation on Spoiler Effects[R].AIAA,91-3214-CP,1991.
[4]Stuckey R A.Flight-Estimated Spoiler Aerodynamics of the F-111C Aircraft[R].AIAA,94-3459-CP,1994.
[5]Hoerner S F,Borsl H V.Fluid Dynamic Lift[M].Mrs.Liselotte A.Hoerner,1985:10-14,10-22.
[2]McLachlan B G,Karamcheti K.An Experimental Study of Airfoil-Spoiler Aerodynamics.NASA Contractor Report177328,1985.
[3]Al-Bahi,A M,Ghazi M A.An experimental Investigation on Spoiler Effects[R].AIAA,91-3214-CP,1991.
[4]Stuckey R A.Flight-Estimated Spoiler Aerodynamics of the F-111C Aircraft[R].AIAA,94-3459-CP,1994.
[5]Hoerner S F,Borsl H V.Fluid Dynamic Lift[M].Mrs.Liselotte A.Hoerner,1985:10-14,10-22.