改进的横流风扇翼型气动特性及参数分析
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- 英文论文题名：Aerodynamic Characteristics and Parameters Analysis of an Improved Cross Flow Fan Airfoil
- 论文作者：孙敏 ; 朱清华
- 英文论文作者：Sun Min ; Zhu Qinghua ; National Laboratory of Science and Technology on Rotorcraft Aeromechanics ; Nanjing University of Aeronautics & Astronautics
- 年：2016
- 作者机构：南京航空航天大学直升机旋翼动力学国家级重点实验室;
- 论文关键词：横流风扇翼型 ; 数值分析 ; 气动特性 ; 参数分析
- 英文论文关键词：cross flow fan airfoil ; numerical simulation ; shape optimization
- 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
- 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：7
- 文件大小：2718k
- 原文格式：O
- 会议级别：全国
摘要
基于RNCκ-ε湍流模型和滑移网格技术数模拟了横流风扇翼型流场特征和气动力系数变化,进行了固定面前后缘高度和叶片外形优化分析,得出High与叶尖距旋转中心距离比值约为0.455、Angle 15°~20°时为固定面前后缘高度的最优范围,叶片长度与叶尖距旋转中心的比值为0.227且安装角为0度的薄叶片升力系数和推力系数较高,为横流风扇翼型的优化提供了依据。
Based on RNG k-ε turbulent model and sliding mesh technology numerical simulate the cross flow fan airfoil flow characteristics and variation of aerodynamic force coefficient,the height of the front and back edge of the airfoil and the shape of the blade are optimized and analyzed,come to the conclusion that when the ratio of "High" with the distance the tip of blade from the rotation center is about 0.455 and angle is 15 degrees to 20 degrees,the height of the front and back edge of the airfoil is the optimum.Lift coefficient and thrust coefficient of thin blade that Ratio of blade length with tip from the center of rotation 0.227 and installation angle of 0 degrees is high,it provides the basis for the optimization of the cross flow fan airfoil.
Based on RNG k-ε turbulent model and sliding mesh technology numerical simulate the cross flow fan airfoil flow characteristics and variation of aerodynamic force coefficient,the height of the front and back edge of the airfoil and the shape of the blade are optimized and analyzed,come to the conclusion that when the ratio of "High" with the distance the tip of blade from the rotation center is about 0.455 and angle is 15 degrees to 20 degrees,the height of the front and back edge of the airfoil is the optimum.Lift coefficient and thrust coefficient of thin blade that Ratio of blade length with tip from the center of rotation 0.227 and installation angle of 0 degrees is high,it provides the basis for the optimization of the cross flow fan airfoil.
引文
[1]孟琳,叶永强,李楠.扇翼飞行器的研究进展和应用前景[J].航空学报,2015,36(8):2651-2661.
[2]Toffolo A,Lazzaretto A Martegani.An Experimental Investigation of the Flow Field Pattern Within the Impeller of a Cross Flow Fan[J].Experimental Thermal and Fluid Science,2004,29(1)53-64.
[3]Deepthi Duddempudi,Yu feng Yao.Computational Flow over Generic Fan-Wing Airfoil[J].Aircraft Engineering and Aerospace Technology,2007,79(3):238-244.
[4]S Askari,M H Shojaeefard.Numerical Simulation of Flow over an Airfoil with a Cross Flow Fan as a Lift Generating Member in a New Aircraft Model[J].Aircraft Engineering and Aerospace Technology,2009,81(1):56-64.
[5]O Ahad,F M R Graham.Flight Simulation and Testing of the Fan Wing Experimental Aircraft[J].Aircraft Engineering and Aerospace Technology,2007,79(2):131-136.
[6]S Askari,H Shojaeefard.Shape Optimization of the Airfoil Comprising a Cross Flow Fan[J].Aircraft Engineering and Aerospace Technology,2009,81(5):407-415.
[7]Salar Askari and M H Shojaeefard.Experimental and Numerical Study of Airfoil in Combination with a Cross Flow Fan[J].Journal of Aerospace Engineering,2012,227(7):1173-1187.
[8]王福军.计算流体动力学分析-CFD软件原理与应用[M].北京:清华大学出版社.
[9]George R Seyfang.Fanwing—Developments and Applications[C].28 International congress of the aeronautical sciences,2012.
[10]Deepthi Duddempudi,Yu feng Yao,David Edmondson.CFD investigation of flow over a generic fanwing airfoil[C].43rd AIAA Aerospace Sciences Meeting and Exhibit,2005-636.
[11]牛中国,蒋甲力,李周复.扇翼飞机二维机翼数值模拟分析研究[C].中国航空学会2007年学术年会.2007.
[12]蒋甲力,牛中国,刘杰.扇翼飞行器机翼布局研究[J].航空科学技术,2009(3):30-35.
[2]Toffolo A,Lazzaretto A Martegani.An Experimental Investigation of the Flow Field Pattern Within the Impeller of a Cross Flow Fan[J].Experimental Thermal and Fluid Science,2004,29(1)53-64.
[3]Deepthi Duddempudi,Yu feng Yao.Computational Flow over Generic Fan-Wing Airfoil[J].Aircraft Engineering and Aerospace Technology,2007,79(3):238-244.
[4]S Askari,M H Shojaeefard.Numerical Simulation of Flow over an Airfoil with a Cross Flow Fan as a Lift Generating Member in a New Aircraft Model[J].Aircraft Engineering and Aerospace Technology,2009,81(1):56-64.
[5]O Ahad,F M R Graham.Flight Simulation and Testing of the Fan Wing Experimental Aircraft[J].Aircraft Engineering and Aerospace Technology,2007,79(2):131-136.
[6]S Askari,H Shojaeefard.Shape Optimization of the Airfoil Comprising a Cross Flow Fan[J].Aircraft Engineering and Aerospace Technology,2009,81(5):407-415.
[7]Salar Askari and M H Shojaeefard.Experimental and Numerical Study of Airfoil in Combination with a Cross Flow Fan[J].Journal of Aerospace Engineering,2012,227(7):1173-1187.
[8]王福军.计算流体动力学分析-CFD软件原理与应用[M].北京:清华大学出版社.
[9]George R Seyfang.Fanwing—Developments and Applications[C].28 International congress of the aeronautical sciences,2012.
[10]Deepthi Duddempudi,Yu feng Yao,David Edmondson.CFD investigation of flow over a generic fanwing airfoil[C].43rd AIAA Aerospace Sciences Meeting and Exhibit,2005-636.
[11]牛中国,蒋甲力,李周复.扇翼飞机二维机翼数值模拟分析研究[C].中国航空学会2007年学术年会.2007.
[12]蒋甲力,牛中国,刘杰.扇翼飞行器机翼布局研究[J].航空科学技术,2009(3):30-35.