四参数变弯度翼型的气动特性分析与优化设计

保女子; 彭叶辉; 冯和英; 杨成浩

doi:10.13433/j.cnki.1003-8728.20200605

四参数变弯度翼型的气动特性分析与优化设计

doi: 10.13433/j.cnki.1003-8728.20200605

1.
湖南科技大学数学与计算科学学院，湖南湘潭　411201
2.
湖南科技大学机械设备健康维护湖南省重点实验室，湖南湘潭　411201

基金项目: 国家自然科学基金项目（51875194）与湖南省自然科学基金项目（2020JJ4306）

详细信息

作者简介:
保女子（1996−），硕士研究生，研究方向为计算数学， baonvzi0216@163.com

通讯作者:
彭叶辉，副教授，硕士生导师，pengyehui@hnust.edu.cn

中图分类号: V211
计量
- 文章访问数: 198
- HTML全文浏览量: 164
- PDF下载量: 33
- 被引次数: 0
出版历程
- 收稿日期: 2021-04-08
- 刊出日期: 2023-02-25

Aerodynamic Characteristic Analysis and Optimization Design of Four-parameter Variable Camber Airfoil

1.
School of Mathematics and Computational Science, Hunan University of Science and Technology, Xiangtan 411201, Hu'nan, China
2.
Hunan Provincial Key Laboratory of Health Maintenance for Mechanical Equipment, Hunan University of Science and Technology, Xiangtan 411201, Hu'nan, China

摘要

摘要: 针对NACA 0012翼型，在马赫数为0.176的来流条件下，首先利用数值模拟研究了翼型前缘下弯角度、前缘偏转位置、后缘下弯角度和后缘偏转位置等因素对翼型气动性能的影响规律；其次，以升阻比为目标，上述4个因素为设计变量，利用神经网络建立升阻比与4个设计变量间的预测模型；然后，充分考虑优化精度和神经网络训练数据库的计算量，构造了一种翼型优化过程与神经网络预测耦合的迭代优化策略，基于该优化策略得到最优变弯度翼型构型。对比优化翼型和原始翼型，升阻比提高约22%，较大程度改善了翼型的气动特性；并且通过远场噪声分析，发现优化翼型表现出了较好的声学性能，在1 000 Hz附近单音噪声最大可降低12 dB。
- 变弯度 /
- 偏转位置 /
- 升阻比 /
- 神经网络 /
- 气动性能
Abstract: Taking the NACA 0012 airfoil as research object,the flight condition selects 0.176 Mach number of incoming flow. Firstly, the influences of the different factors on the aerodynamic performance of the airfoil have been investigated by the numerical simulation, such as the downward bending angle and deflection position of the leading and trailing edgefor the airfoil and so on. Secondly, the prediction model between the object variable lift-drag ratio and the above four design variables is established by the neural network. Then under consideration of the optimization precision and the computation cost of neural network training database, an iterative optimization strategy is present, which is coupled with the neural network and optimization process. Furthermore, the optimal variable camber airfoil configuration is obtained based on the optimization strategy. Compared with the original airfoil, the optimized one increases the lift-drag ratioby about the 22%, and the aerodynamic characteristics of airfoil have been greatly improved. Moreover, by far field noise analysis, it is found that the optimized airfoil has better acoustic performance, and the tonal noise of around 1 000 Hz can be reduced by up to 12 dB.
- variable camber /
- deflection position /
- lift-drag ratio /
- neural network /
- aerodynamic performance

HTML全文

图 1 翼型网格

下载: 全尺寸图片幻灯片

图 2 网格无关性验证

下载: 全尺寸图片幻灯片

图 3 翼型表面的压力系数分布对比

下载: 全尺寸图片幻灯片

图 4 翼型变弯度示意图

下载: 全尺寸图片幻灯片

图 5 翼型不同前缘下弯角度的气动性能

下载: 全尺寸图片幻灯片

图 6 翼型不同前缘偏转位置下的气动性能

下载: 全尺寸图片幻灯片

图 7 翼型不同后缘下弯角度的气动性能

下载: 全尺寸图片幻灯片

图 8 翼型不同后缘偏转位置下的气动性能

下载: 全尺寸图片幻灯片

图 9 神经网络逼近与优化耦合算法

下载: 全尺寸图片幻灯片

图 10 神经网络回归分析图

下载: 全尺寸图片幻灯片

图 11 翼型优化前后气动性能对比

下载: 全尺寸图片幻灯片

图 12 翼型表面压力云图

下载: 全尺寸图片幻灯片

图 13 翼型压力系数分布

下载: 全尺寸图片幻灯片

图 14 翼型优化前后声压级频谱对比

下载: 全尺寸图片幻灯片

图 15 翼型湍动能云图

下载: 全尺寸图片幻灯片

图 16 翼型速度脉动云图

下载: 全尺寸图片幻灯片

图 17 翼型涡量云图

下载: 全尺寸图片幻灯片

表 1 不同前缘下弯角度

翼型	前缘下弯角度	翼型	前缘下弯角度
${\theta _{LE} }{\text{-}}5^\circ$	5°	${\theta _{LE} }{\text{-}}15^\circ$	15°
${\theta _{LE} }{\text{-}}10^\circ$	10°	${\theta _{LE} }{\text{-}}20^\circ$	20°

下载: 导出CSV

表 2 不同前缘偏转位置

翼型	前缘偏转位置
${H_{LE} } {\text{-}} 0.1c$	$ 0.1c $
${H_{LE} } {\text{-}} 0.2c$	$ 0.2c $
${H_{LE} } {\text{-}} 0.3c$	$ 0.3c $
${H_{LE} } {\text{-}} 0.4c$	$ 0.4c $

下载: 导出CSV

表 3 不同后缘下弯角度

翼型	后缘下弯角度
$ {\theta _{TE}} {\text{-}} 5^\circ $	5°
$ {\theta _{TE}}{\text{-}} 10^\circ $	10°
$ {\theta _{TE}} {\text{-}} 15^\circ $	15°
$ {\theta _{TE}} {\text{-}}20^\circ $	20°

下载: 导出CSV

表 4 不同后缘偏转位置

翼型	后缘偏转位置
$ {H_{TE}} {\text{-}} 0.6c $	0.6c
$ {H_{TE}} {\text{-}} 0.7c $	0.7c
$ {H_{TE}} {\text{-}} 0.8c $	0.8c
$ {H_{TE}} {\text{-}} 0.9c $	0.9c

下载: 导出CSV

表 5 优化结果

设计变量	优化结果
前缘偏转位置	0.38c
后缘偏转位置	0.9c
前缘下弯角度	8.11°
后缘下弯角度	7.21°

下载: 导出CSV

表 6 优化前后气动特性对比

气动性能	原始翼型	优化翼型	增长率/%
$ {C_L} $	0.99924	1.12347	12.423
$ {C_D} $	0.02087	0.01923	−7.86
$ K $	47.8793	58.4227	22

下载: 导出CSV

参考文献(35)

[1]	何萌, 杨体浩, 白俊强, 等. 基于后缘襟翼偏转的大型客机变弯度技术减阻收益[J]. 航空学报, 2020, 41(7): 123462 HE M, YANG T H, BAI J Q, et al. Drag reduction benefits of variable camber technology of airliner based on trailing-edge flap deflection[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(7): 123462 (in Chinese)
[2]	LEBOFSKY S, TING E, NGUYEN N. Aeroelastic modeling and drag optimization of flexible wing aircraft with variable camber continuous trailing edge flap[C]//32nd AIAA Applied Aerodynamics Conference. Atlanta: American Institute of Aeronautics and Astronautics, 2014
[3]	URNES J M, MORRIS C, SHEAHAN J, et al. Control system design for a variable camber continuous trailing edge flap system on an elastic wing[C]//55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Maryland: American Institute of Aeronautics and Astronautics, 2014
[4]	URNES J, NGUYEN N, IPPOLITO C, et al. A mission adaptive variable camber flap control system to optimize high lift and cruise lift to drag ratios of future N + 3 transport aircraft[C]//51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Grapevine, Texas: American Institute of Aeronautics and Astronautics, 2013
[5]	白鹏, 陈钱, 徐国武, 等. 智能可变形飞行器关键技术发展现状及展望[J]. 空气动力学学报, 2019, 37(3): 426-443 BAI P, CHEN Q, XU G W, et al. Development status of key technologies and expectation about smart morphing aircraft[J]. Acta Aerodynamica Sinica, 2019, 37(3): 426-443 (in Chinese)
[6]	杨文超,杨剑挺,王进,等.变弯度机翼准定常流动分离特性的实验研究[J].中国科学:物理学力学天文学,2012,42(5):531-537. Yang W C, Yang J T, Wang J, et al. Experimental investigation on the quasi-steady flow separation behaviors of a variable camber wing[J]. SCIENCE CHINA Physics, Mechanics & Astronomy, 2012, 42: 531–537 (in Chinese)
[7]	LEE D S, GONZALEZ L F, PERIAUX J, et al. Robust aerodynamic design optimisation of morphing aerofoil/wing using distributed MOGA[C]//Proceedings of the 28th Congress of the International Council of the Aeronautical Sciences. Brisbane: The International Council of the Aeronautical Sciences, 2012
[8]	MOLINARI G, QUACK M, ARRIETA A F, et al. Design, realization and structural testing of a compliant adaptable wing[J]. Smart Materials and Structures, 2015, 24(10): 105027 doi: 10.1088/0964-1726/24/10/105027
[9]	MOLINARI G, QUACK M, DMITRIEV V, et al. Aero-structural optimization of morphing airfoils for adaptive wings[J]. Journal of Intelligent Material Systems and Structures, 2011, 22(10): 1075-1089 doi: 10.1177/1045389X11414089
[10]	KAUL U K, NGUYEN N T. Drag optimization study of variable camber continuous trailing edge flap (VCCTEF) using overflow[C]//32nd AIAA Applied Aerodynamics Conference. Atlanta: American Institute of Aeronautics and Astronautics, 2014
[11]	BURDETTE D A, KENWAY G K W, MARTINS J R R A. Aerostructural design optimization of a continuous morphing trailing edge aircraft for improved mission performance[C]//17th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference. Washington: American Institute of Aeronautics and Astronautics, 2016
[12]	BURDETTE JR D A. High-fidelity aerostructural design optimization of transport aircraft with continuous morphing trailing edge technology[D]. Ann Arbor: University of Michigan, 2017
[13]	YOKOZEKI T, SUGIURA A, HIRANO Y. Development and wind tunnel test of variable camber morphing wing[C]//22nd AIAA/ASME/AHS Adaptive Structures Conference. National Harbor, Maryland: American Institute of Aeronautics and Astronautics, 2014
[14]	陈钱, 白鹏, 尹维龙, 等. 可连续光滑偏转后缘的变弯度翼型气动特性分析[J]. 空气动力学学报, 2010, 28(1): 46-53 doi: 10.3969/j.issn.0258-1825.2010.01.007 CHEN Q, BAI P, YIN W L, et al. Analysis on the aerodynamic characteristics of variable camber airfoils with continuous smooth morphing trailing edge[J]. Acta Aerodynamica Sinica, 2010, 28(1): 46-53 (in Chinese) doi: 10.3969/j.issn.0258-1825.2010.01.007
[15]	陆维爽, 刘沛清, 郭昊. 前缘下垂远场低频宽频噪声特性[J]. 航空学报, 2019, 40(10): 123152 LU W S, LIU P Q, GUO H. Characteristics of low frequency broadband noise for leading-edge droop nose measured in a far-field[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(10): 123152 (in Chinese)
[16]	杨小权, 孙一峰, 杨士普, 等. 前缘下垂增升装置气动特性和噪声特性研究[C]//第九届全国流体力学学术会议论文摘要集. 南京: 中国力学学会, 2016: 434-435 YANG X Q, SUN Y F, YANG S P, et al. Research on the aerodynamic and noise characteristics of the leading-edge droop-increasing device[C]//Proceedings of the Ninth National Conference on Fluid Mechanics. Nanjing: Chinese Society of Theoretical and Applied Mechanics, 2016: 434-435 (in Chinese)
[17]	王斌, 郝璇, 郭少杰, 等. 宽体客机巡航机翼变弯度减阻技术[J]. 空气动力学学报, 2019, 37(6): 974-982 doi: 10.7638/kqdlxxb-2017.0215 WANG B, HAO X, GUO S J, et al. Cruise drag reduction of variable camber wing of wide-body civil transport[J]. Acta Aerodynamica Sinica, 2019, 37(6): 974-982 (in Chinese) doi: 10.7638/kqdlxxb-2017.0215
[18]	FINCHAM J H S, FRISWELL M I. Aerodynamic optimisation of a camber morphing aerofoil[J]. Aerospace Science and Technology, 2015, 43: 245-255 doi: 10.1016/j.ast.2015.02.023
[19]	田晓虎, 张彬乾, 沈冬. 引入最优顶点的混合方法及其在翼型优化设计中的应用[J]. 机械科学与技术, 2012, 31(12): 2010-2013 doi: 10.13433/j.cnki.1003-8728.2012.12.016 TIAN X H, ZHANG B Q, SHEN D. Hybrid optimization method based on the best vertex and its application to optimization design of airfoil[J]. Mechanical Science and Technology for Aerospace Engineering, 2012, 31(12): 2010-2013 (in Chinese) doi: 10.13433/j.cnki.1003-8728.2012.12.016
[20]	辛尊, 丁运亮. 高速民用运输机机翼的多学科设计优化[J]. 机械科学与技术, 2012, 31(1): 79-82 doi: 10.13433/j.cnki.1003-8728.2012.01.032 XIN Z, DING Y L. Multi-disciplinary design optimization of a high-speed civil transporter wing[J]. Mechanical Science and Technology for Aerospace Engineering, 2012, 31(1): 79-82 (in Chinese) doi: 10.13433/j.cnki.1003-8728.2012.01.032
[21]	王清, 招启军. 基于遗传算法的旋翼翼型综合气动优化设计[J]. 航空动力学报, 2016, 31(6): 1486-1945 doi: 10.13224/j.cnki.jasp.2016.06.026 WANG Q, ZHAO Q J. Synthetical optimization design of rotor airfoil by genetic algorithm[J]. Journal of Aerospace Power, 2016, 31(6): 1486-1945 (in Chinese) doi: 10.13224/j.cnki.jasp.2016.06.026
[22]	何磊, 钱炜祺, 刘滔, 等. 基于深度学习的翼型反设计方法[J]. 航空动力学报, 2020, 35(9): 1909-1917 doi: 10.13224/j.cnki.jasp.2020.09.013 HE L, QIAN W Q, LIU T, et al. Inverse design method of airfoil based on deep learning[J]. Journal of Aerospace Power, 2020, 35(9): 1909-1917 (in Chinese) doi: 10.13224/j.cnki.jasp.2020.09.013
[23]	FATAHIAN E, NICHKOOHI A L, SALARIAN H, et al. Effects of the hinge position and suction on flow separation and aerodynamic performance of the NACA 0012 airfoil[J]. Journal of the Brazilian Society of Mechanical Sciences and Engineering, 2020, 42(2): 86 doi: 10.1007/s40430-020-2170-4
[24]	陈懋章. 粘性流体动力学基础[M]. 北京: 高等教育出版社, 2002 CHEN M Z. Fundamentals of viscous fluid dynamics[M]. Beijing: Higher Education Press, 2002 (in Chinese)
[25]	马娜, 袁启龙, 周新涛, 等. 风力发电机叶片气动特性数值模拟[J]. 机械科学与技术, 2014, 33(10): 1473-1478 doi: 10.13433/j.cnki.1003-8728.2014.1007 MA N, YUAN Q L, ZHOU X T, et al. Numerical simulation of aerodynamic performance for wind turbine blade[J]. Mechanical Science and Technology for Aerospace Engineering, 2014, 33(10): 1473-1478 (in Chinese) doi: 10.13433/j.cnki.1003-8728.2014.1007
[26]	LADSON C L, HILL A S, JOHNSON JR W G. Pressure distributions from high Reynolds number transonic tests of an NACA 0012 airfoil in the Langley 0.3-meter transonic cryogenic tunnel[R]. Hampton, VA: National Aeronautics and Space Administration, Langley Research Center, 1987
[27]	刘加伟, 柳兆涛, 丁仕洪, 等. 等离子体热效应对NACA0012翼型增升减阻的研究[J]. 推进技术, 2020, 41(5): 1055-1062 doi: 10.13675/j.cnki.tjjs.190574 LIU J W, LIU Z T, DING S H, et al. Study on lift enhancement and drag reduction of naca0012 airfoil under plasma thermal effect[J]. Journal of Propulsion Technology, 2020, 41(5): 1055-1062 (in Chinese) doi: 10.13675/j.cnki.tjjs.190574
[28]	SCHATZMAN N L. Aerodynamics and aeroacoustic sources of a coaxial rotor[R]. 2018
[29]	陆维爽, 田云, 刘沛清, 等. GAW-1翼型前后缘变弯度气动性能研究[J]. 航空学报, 2016, 37(2): 437-450 LU W S, TIAN Y, LIU P Q, et al. Aerodynamic performance of gaw-1 airfoil leading-edge and trailing-edge variable camber[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(2): 437-450 (in Chinese)
[30]	高超, 贾娅娅, 刘庆宽. 相对厚度对翼型气动特性的影响研究[J]. 工程力学, 2020, 37(S1): 380-386 doi: 10.6052/j.issn.1000-4750.2019.04.S062 GAO C, JIA Y Y, LIU Q K. Effect of relative thickness on aerodynamic performance of airfoil[J]. Engineering Mechanics, 2020, 37(S1): 380-386 (in Chinese) doi: 10.6052/j.issn.1000-4750.2019.04.S062
[31]	孙召成, 李增亮, 徐朝政, 等. 潮流能水轮机翼型升阻比与空化性能优化研究[J]. 太阳能学报, 2019, 40(12): 3331-3338 SUN Z C, LI Z L, XU C Z, et al. Optimization of lift-drag ratio and cavitation performance for marine current turbine[J]. Acta Energiae Solaris Sinica, 2019, 40(12): 3331-3338 (in Chinese)
[32]	孙召成, 李增亮, 徐朝政, 等. 基于B样条与遗传算法的翼型优化实验研究[J]. 工程热物理学报, 2019, 40(12): 2806-2814 SUN Z C, LI Z L, XU C Z, et al. Airfoil optimization and experimental research based on the b spline and genetic algorithm[J]. Journal of Engineering Thermophysics, 2019, 40(12): 2806-2814 (in Chinese)
[33]	CYBENKO G. Approximation by superpositions of a sigmoidal function[J]. Mathematics of Control, Signals and Systems, 1989, 2(4): 303-314 doi: 10.1007/BF02551274
[34]	ZHAO A M, HUI Z, JIN H C, et al. Analysis on the aerodynamic characteristics of a continuous whole variable camber airfoil[J]. Journal of Physics: Conference Series, 2019, 1215(1): 012005 doi: 10.1088/1742-6596/1215/1/012005
[35]	王秉良, 鲁嘉华, 匡江红, 等. 飞机空气动力学[M]. 北京: 清华大学出版社, 2013 WANG B L, LU J H, KUANG J H, et al. Aircraft aerodynamics[M]. Beijing: Tsinghua University Press, 2013 (in Chinese)