Optimal design of multi-objective aerodynamic performance of leading edge slat
-
摘要:
翼型前缘开缝可抑制翼型大攻角下流动分离，有效提升气动性能。确定缝翼几何参数是改善气动性能的关键，因此基于遗传算法对前缘缝翼进行多目标气动性能优化设计研究。选取NACA 0012进行缝翼几何参数设计，定义缝道宽度、位置、弯曲程度等输入参数范围，通过优化拉丁方方法采样。为提升优化效率，利用样本数据建立输入参数和以升阻力系数为目标参数的代理模型，并通过多目标遗传算法进行全局范围内的目标参数寻优。研究表明：缝道弯曲程度越大，失速后升力系数提升越明显。前缘缝翼增加了上翼面湍动能及翼型前缘上下翼面的压差，改善翼型大攻角下气动性能。优化后翼型，最大升力系数提升12.5%，失速攻角推迟5°。为前缘缝翼气动性能优化设计提供理论参考。
Abstract:Leading edge slat can inhibit the flow separation at large angles of attack and effectively improve the aerodynamic performance. Determining the geometry parameters of slat is vital to improve the aerodynamic performance. Therefore, the aerodynamic performance of leading edge slat was optimized based on multi-objective genetic algorithm. NACA 0012 was selected to design the geometry parameters of slats, and the input parameters such as slat width, position and curves degree were defined. The optimized Latin-hypercube method was used for sampling. The sample data were used to establish the input parameters and the surrogate model with lift and drag coefficient as the target parameters to improve the optimization efficiency, and the multi-objective genetic algorithm was used to optimize the target parameters in the glob-al scope. Results indicated the lift coefficient increased obviously with the large curves degree of slat. Leading-edge slat improved the aerodynamic performance by increasing the turbulent kinetic energy of upper wing sur-face and reducing the pressure coefficient of the front edge of the upper wing. After optimization, the maximum lift coefficient of the airfoil with slat was increased by 12.5% and the stall angle of attack was delayed by 5°. It could provide theoretical support for the optimization design of airfoil aerodynamic performance with slat.
-
图 10 不同缝道宽度样本外特性曲线
Figure 10. Out of sample characteristic curves of different slat widths
图 12 不同缝道位置样本外特性曲线
Figure 12. Out of sample characteristic curves of different slat positions
图 13 不同缝道弯曲程度样本外特性曲线
Figure 13. Out of sample characteristic curves of different slat bending degrees
图 14 不同缝道弯曲程度样本速度、压力分布
Figure 14. Sample velocity and pressure distribution of different slat bending degree
图 16 小攻角下优化翼型与原始翼型对比
Figure 16. Comparison of optimized airfoil and original airfoil at small angle of attack
图 17 失速攻角下优化翼型与原始翼型对比
Figure 17. Comparison of optimized airfoil and original airfoil at stall angle of attack
图 18 大攻角下优化翼型与原始翼型压力系数对比
Figure 18. Comparison of pressure coefficients between optimized airfoil and original airfoil under high angle of attack
表 1 缝翼参数范围
Table 1. Range of slat parameter
m 参数名称 参数范围 缝道弧形半径R 0.025～0.040 缝道宽度b 0.002～0.005 缝道位置坐标x1 0.040～0.060 
下载: 导出CSV
表 2 网格无关性验证
Table 2. Grid independence verification
参数 第1套 第2套 第3套 第4套 第5套 网格数量/104 3 6 12 18 29 升力系数 0.5524 0.5669 0.5666 0.5661 0.5665
下载: 导出CSV
表 3 缝翼网格无关性验证
Table 3. Grid independence verification of slat
参数 第1套 第2套 第3套 第4套 第5套 网格数量/104 8 12 14 18 22 升力系数 0.4689 0.4979 0.4987 0.4966 0. 4980
下载: 导出CSV
表 4 选取样本模型数据
Table 4. Select sample model data
m 编号 缝道
弧形半径
R缝道
宽度b缝道
位置坐标
x1升力
系数Cl阻力
系数Cd样本1 0.40 0.025 0.442 0.46 0.19 样本2 0.384 0.036 0.547 0.54 0.16 样本3 0.329 0.034 0.495 0.59 0.15 样本4 0.337 0.028 0.590 0.70 0.14 样本5 0.266 0.026 0.484 1.14 0.07 样本6 0.376 0.023 0.526 0.57 0.16 样本7 0.305 0.02 0.537 0.76 0.13 样本8 0.274 0.03 0.579 1.16 0.07 样本9 0.313 0.041 0.568 0.68 0.14 样本10 0.361 0.047 0.516 0.53 0.16 样本11 0.368 0.045 0.60 0.58 0.15 样本12 0.258 0.039 0.474 1.28 0.06 样本13 0.392 0.037 0.463 0.46 0.18 样本14 0.353 0.031 0.40 0.46 0.18 样本15 0.250 0.042 0.558 1.35 0.05 样本16 0.345 0.044 0.432 0.48 0.18 样本17 0.290 0.033 0.411 0.65 0.16 样本18 0.321 0.022 0.453 0.61 0.16 样本19 0.282 0.048 0.421 0.60 0.15 样本20 0.297 0.05 0.505 0.64 0.14
下载: 导出CSV
表 5 对比样本参数设计
Table 5. Comparison sample parameter design
m 样本名称 R b x1 样本A 0.00376 0.0023 0.0526 样本B 0.0376 0.0047 0.0526 样本C 0.0376 0.0023 0.0442 样本D 0.0258 0.0023 0.0526
下载: 导出CSV
表 6 选取优化模型数据
Table 6. Select optimization model data
m 最优解 缝道
宽度b缝道弧形
半径R缝道位置
坐标x1优化1 0.00374 0.0250 0.0524 优化2 0.00374 0.0250 0.0522 优化3 0.00371 0.0250 0.0517 优化4 0.00368 0.0251 0.0515 优化5 0.00364 0.0251 0.0515 优化6 0.00353 0.0252 0.0515 优化7 0.00345 0.0252 0.0515
下载: 导出CSV
-
[1] 孙茂,王家禄,连淇祥. 等速上仰翼型尾部流动观察及动态失速机理探讨[J]. 力学学报,1993,25(5): 628-631. SUN Mao,WANG Jialu,LIAN Qixiang. The trailing-edge vortex structure of a constant-rate airfoil and mechanism of dynamic stall[J]. Acta Mechanic Sinica,1993,25(5): 628-631. (in ChineseSUN Mao, WANG Jialu, LIAN Qixiang. The trailing-edge vortex structure of a constant-rate airfoil and mechanism of dynamic stall[J]. Acta Mechanic Sinica, 1993, 25(5): 628-631. (in Chinese) [2] SOHANKAR A,KHODADADI M,RANGRAZ E. Control of fluid flow and heat transfer around a square cylinder by uniform suction and blowing at low Reynolds numbers[J]. Computers & Fluids,2015,109: 155-167. [3] 李潮隆,夏智勋,罗振兵,等. 合成双射流控制水下圆柱绕流流动分离数值模拟研究[J]. 空气动力学学报,2020,38(2): 254-259,267. LI Chaolong,XIA Zhixun,LUO Zhenbing,et al. Numerical study on flow separation of underwater cylinder with dual synthetic jets actuator[J]. Acta Aerodynamica Sinica,2020,38(2): 254-259,267. (in Chinese doi: 10.7638/kqdlxxb-2018.0224LI Chaolong, XIA Zhixun, LUO Zhenbing, et al. Numerical study on flow separation of underwater cylinder with dual synthetic jets actuator[J]. Acta Aerodynamica Sinica, 2020, 38(2): 254-259, 267. (in Chinese) doi: 10.7638/kqdlxxb-2018.0224 [4] 任刘珍,李霖,张梦卓,等. 连续吹喷-抽吸控制方法对圆柱尾流的影响[J]. 兵工学报,2021,42(5): 1016-1022. REN Liuzhen,LI Lin,ZHANG Mengzhuo,et al. Control of wake flow of a circular cylinder by continuous blow and suction[J]. Acta Armamentarii,2021,42(5): 1016-1022. (in Chinese doi: 10.3969/j.issn.1000-1093.2021.05.014REN Liuzhen, LI Lin, ZHANG Mengzhuo, et al. Control of wake flow of a circular cylinder by continuous blow and suction[J]. Acta Armamentarii, 2021, 42(5): 1016-1022. (in Chinese) doi: 10.3969/j.issn.1000-1093.2021.05.014 [5] 马祺敏,王加浩,张洋,等. 风力机翼型仿生襟翼的结构参数优化设计及气动性研究[J]. 西安交通大学学报,2022,56(11): 31-40. MA Qimin,WANG Jiahao,ZHANG Yang,et al. Research on optimized design of structural parameters and aerodynamics of wind turbine airfoil with bionic flap[J]. Journal of Xi’an Jiaotong University,2022,56(11): 31-40. (in Chinese doi: 10.7652/xjtuxb202211004MA Qimin, WANG Jiahao, ZHANG Yang, et al. Research on optimized design of structural parameters and aerodynamics of wind turbine airfoil with bionic flap[J]. Journal of Xi’an Jiaotong University, 2022, 56(11): 31-40. (in Chinese) doi: 10.7652/xjtuxb202211004 [6] 吴立明,姜怡欣,刘小民,等. 几种仿生翼型动态失速特性的数值分析[J]. 西安交通大学学报,2022,56(9): 1-9. WU Liming,JIANG Yixin,LIU Xiaomin,et al. Numerical analysis of dynamic stall characteristics of several bionic airfoils[J]. Journal of Xi’an Jiaotong University,2022,56(9): 1-9. (in ChineseWU Liming, JIANG Yixin, LIU Xiaomin, et al. Numerical analysis of dynamic stall characteristics of several bionic airfoils[J]. Journal of Xi’an Jiaotong University, 2022, 56(9): 1-9. (in Chinese) [7] 刘中元,褚胡冰,陈迎春,等. 前缘缝翼开缝改善增升装置失速特性研究[J]. 空气动力学报,2023,41(2): 21-28. LIU Zhongyuan,CHU Hubing,CHEN Yingchun,et al. Stall characteristics of high-lift device Improved by slotting on lead-ing-edge slat[J]. Acta Aerodynamica Sinica,2023,41(2): 21-28. (in ChineseLIU Zhongyuan, CHU Hubing, CHEN Yingchun, et al. Stall characteristics of high-lift device Improved by slotting on lead-ing-edge slat[J]. Acta Aerodynamica Sinica, 2023, 41(2): 21-28. (in Chinese) [8] 冯蕴雯,张家乐,薛小锋,等. 基于干涉接触的缝翼尾缘结构设计与分析[J]. 北京航空航天大学学报,2023,49(4): 761-767. FENG Yunwen,ZHANG Jiale,XUE Xiaofeng,et al. Design and analysis of trailing edge structure of slats based on inter-ference contact[J]. Journal of Beijing University of Aeronautics and Astronautics,2023,49(4): 761-767. (in ChineseFENG Yunwen, ZHANG Jiale, XUE Xiaofeng, et al. Design and analysis of trailing edge structure of slats based on inter-ference contact[J]. Journal of Beijing University of Aeronautics and Astronautics, 2023, 49(4): 761-767. (in Chinese) [9] 杜刚. 风力机专用翼型动态失速数值模拟研究[C]//2013中国力学大会论文集,陕西 西安: 中国力学学会,2013: 294. DU Gang. Numerical simulation study on dynamic stall of wind turbine specific airfoil [C]//Proceedings of the 2013 Chinese Mechanics Conference,Xi’an Shaanxi: Chinese Society of Mechanics,2013: 294. (in ChineseDU Gang. Numerical simulation study on dynamic stall of wind turbine specific airfoil [C]//Proceedings of the 2013 Chinese Mechanics Conference, Xi’an Shaanxi: Chinese Society of Mechanics, 2013: 294. (in Chinese) [10] 王鑫磊,李生伟,林长亮. 前缘缝翼构型平尾直升机气动特性分析[J]. 南京航空航天大学学报,2020,52(2): 288-293. WANG Xinlei,LI Shengwei,LIN Changliang. Aerodynamic characteristics of helicopter with leading-edge slatted horizontal tail[J]. Journal of Nanjing University of Aeronautics & Astronautics,2020,52(2): 288-293. (in ChineseWANG Xinlei, LI Shengwei, LIN Changliang. Aerodynamic characteristics of helicopter with leading-edge slatted horizontal tail[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2020, 52(2): 288-293. (in Chinese) [11] 姚雪波. 前缘缝翼结构设计分析[J]. 民用飞机设计与研究,1996(4): 18-22,27. [12] WANG Haipeng,JIANG Xiao,CHAO Yun,et al. Effects of leading edge slat on flow separation and aerodynamic performance of wind turbine[J]. Energy,2019,182: 988-998. doi: 10.1016/j.energy.2019.06.096 [13] 张志强,崔可,贺雅婷. 翼型结构边界层吹气控制的数值研究[J]. 山东工业技术,2015(13): 224-225. ZHANG Zhiqiang,CUI Ke,HE Yating. Numerical study on boundary layer blowing control of airfoil structure[J]. Journal of Shandong Industrial Technology,2015(13): 224-225. (in ChineseZHANG Zhiqiang, CUI Ke, HE Yating. Numerical study on boundary layer blowing control of airfoil structure[J]. Journal of Shandong Industrial Technology, 2015(13): 224-225. (in Chinese) [14] OLSON L E,MCGOWAN P R,GUEST C J. Leading-edge slat optimization for maximum airfoil lift. United States: NASA,1979. [15] TUNG C,MCALISTER K W,CARR L W,et al. The quest for stall-free dynamic lift[R]. California: NASA. Ames Research Center,Physics of Forced Unsteady Separation,1992. [16] 徐学昊,叶舟,韩彦军,等. 翼缝改形对翼型流动分离控制影响[J]. 热能动力工程,2020,35(12): 169-176. XU Xuehao,YE Zhou,HAN Yanjun,et al. Slot modifica-tion influence on the flow separation control of airfoil[J]. Journal of Engineer for Thermal Enegry and Power,2020,35(12): 169-176. (in ChineseXU Xuehao, YE Zhou, HAN Yanjun, et al. Slot modifica-tion influence on the flow separation control of airfoil[J]. Journal of Engineer for Thermal Enegry and Power, 2020, 35(12): 169-176. (in Chinese) [17] 邓一菊,廖振荣,段卓毅. 前缘缝翼内型的气动设计研究[J]. 空气动力学学报,2014,32(3): 400-404. DENG Yiju,LIAO Zhenrong,DUAN Zhuoyi. Aerodynamic design research on slat coves[J]. Acta Aerodynamica Sinica,2014,32(3): 400-404. (in ChineseDENG Yiju, LIAO Zhenrong, DUAN Zhuoyi. Aerodynamic design research on slat coves[J]. Acta Aerodynamica Sinica, 2014, 32(3): 400-404. (in Chinese) [18] ZAKI A,ABDELRAHMAN M A,AYAD S S,et al. Effects of leading edge slat on the aerodynamic performance of low Reynolds number horizontal axis wind turbine[J]. Energy,2022,239: 122338. doi: 10.1016/j.energy.2021.122338 [19] LI Yang,WANG Haipeng,WU Zhigang. Aerodynamic characteristic of wind turbine with the leading edge slat and Microtab[J]. Sustainable Energy Technologies and Assessments,2022,52: 101957. doi: 10.1016/j.seta.2022.101957 [20] 赵明智,曹慧晶,张明明,等. 锯齿尾缘降噪翼型优化设计研究[J]. 工程热物理学报,2022,43(2): 384-389. ZHAO Mingzhi,CAO Huijing,ZHANG Mingming,et al. Optimal design of airfoil with trailing edge serration[J]. Journal of Engineering Thermophysics,2022,43(2): 384-389. (in ChineseZHAO Mingzhi, CAO Huijing, ZHANG Mingming, et al. Optimal design of airfoil with trailing edge serration[J]. Journal of Engineering Thermophysics, 2022, 43(2): 384-389. (in Chinese) [21] 王璐瑶,于佳鑫,王晓东,等. 基于代理模型与遗传算法的翼型优化设计方法研究[J]. 风机技术,2021,63(6): 69-75. WANG Luyao,YU Jiaxin,WANG Xiaodong,et al. Investigations on airfoil optimization method based on surrogate model and genetic algorithm[J]. Chinese Journal of Turbomachinery,2021,63(6): 69-75. (in ChineseWANG Luyao, YU Jiaxin, WANG Xiaodong, et al. Investigations on airfoil optimization method based on surrogate model and genetic algorithm[J]. Chinese Journal of Turbomachinery, 2021, 63(6): 69-75. (in Chinese) [22] 倪昂修,张宇飞,陈海昕. NSGA-Ⅱ算法的改进及其在多段翼型缝道参数优化中的应用[J]. 空气动力学学报,2014,32(2): 252-257. NI Angxiu,ZHANG Yufei,CHEN Haixin. An Improvement to NSGA-Ⅱ algorithm and its application in optimization design of multi-element airfoil[J]. Acta Aerodynamica Sinica,2014,32(2): 252-257. (in Chinese doi: 10.7638/kqdlxxb-2013.0095NI Angxiu, ZHANG Yufei, CHEN Haixin. An Improvement to NSGA-Ⅱ algorithm and its application in optimization design of multi-element airfoil[J]. Acta Aerodynamica Sinica, 2014, 32(2): 252-257. (in Chinese) doi: 10.7638/kqdlxxb-2013.0095 [23] 常晟铭,丁恩宝,王超,等. 基于NSGA-Ⅱ遗传算法的二维船舵翼型优化研究[C]// 第十六届全国水动力学学术会议暨第三十二届全国水动力学研讨会论文集(下册). 江苏 无锡: 中国水动力学会,2021: 532-542. CHANG Shengming,DING Enbao,WANG Chao,et al. Research on optimization of two dimensional ship rudder airfoil based on NSGA-Ⅱ genetic algorithm [C]//Proceedings of the 16th National Hydrodynamics Academic Conference and the 32nd National Hydrodynamics Symposium (Volume 2). Wuxi,Jiangsu: Chinese Society of Hydrodynamics,2021: 532-542 (in ChineseCHANG Shengming, DING Enbao, WANG Chao, et al. Research on optimization of two dimensional ship rudder airfoil based on NSGA-Ⅱ genetic algorithm [C]//Proceedings of the 16th National Hydrodynamics Academic Conference and the 32nd National Hydrodynamics Symposium (Volume 2). Wuxi, Jiangsu: Chinese Society of Hydrodynamics, 2021: 532-542 (in Chinese) [24] 许常悦,孙智,倪竹青. 一方程和两方程尺度自适应模拟方法的比较[C]// 中国力学大会-2017暨庆祝中国力学学会成立60周年大会论文集(B). 北京: 中国力学学会,2017: 2-12. XU Changyue,SUN Zhi,NI Zhuqing. Comparison of one equation and two equation scale adaptive simulation methods [C]//Proceedings of the Chinese Mechanics Conference-2017 and the 60th Anniversary Celebration of the Establishment of the Chinese Society of Mechanics (B) Beijing: Chinese Society of Mechanics,2017: 2-12. (in ChineseXU Changyue, SUN Zhi, NI Zhuqing. Comparison of one equation and two equation scale adaptive simulation methods [C]//Proceedings of the Chinese Mechanics Conference-2017 and the 60th Anniversary Celebration of the Establishment of the Chinese Society of Mechanics (B) Beijing: Chinese Society of Mechanics, 2017: 2-12. (in Chinese) [25] SHELDAHL R E,KLIMAS P C. Aerodynamic characteristics of seven symmetrical airfoil sections through 180-degree angle of attack for use in aerodynamic analysis of vertical axis wind turbines[R]. Albuquerque,US: Sandia National Laboratories,1981. [26] NAIN P K S,DEB K. Computationally effective search and optimization procedure using coarse to fine approximations[C]//The 2003 Congress on Evolutionary Computation,2003. CEC '03. Piscataway,US: IEEE,2004: 2081-2088. [27] 叶鹏程,潘光,高山. 一种快速优化拉丁超立方试验设计方法[J]. 西北工业大学学报,2019,37(4): 714-723. YE Pengcheng,PAN Guang,GAO Shan. A fast optimization method for experimental design of Latin Hypercube[J]. Journal of Northwestern Polytechnical University,2019,37(4): 714-723. (in Chinese doi: 10.3969/j.issn.1000-2758.2019.04.010YE Pengcheng, PAN Guang, GAO Shan. A fast optimization method for experimental design of Latin Hypercube[J]. Journal of Northwestern Polytechnical University, 2019, 37(4): 714-723. (in Chinese) doi: 10.3969/j.issn.1000-2758.2019.04.010 [28] 刘晓路,陈英武,荆显荣,等. 优化拉丁方试验设计方法及其应用[J]. 国防科技大学学报,2011,35(5): 73-77. LIU Xiaolu,CHEN Yingwu,JING Xianrong,et al. Optimized Latin hypercube sampling method and its application[J]. Journal of National University of Defense Technology,2011,35(5): 73-77. (in Chinese doi: 10.3969/j.issn.1001-2486.2011.05.015LIU Xiaolu, CHEN Yingwu, JING Xianrong, et al. Optimized Latin hypercube sampling method and its application[J]. Journal of National University of Defense Technology, 2011, 35(5): 73-77. (in Chinese) doi: 10.3969/j.issn.1001-2486.2011.05.015 [29] 韩忠华. Kriging模型及代理优化算法研究进展[J]. 航空学报,2016,37(11): 3197-3225. HAN Zhonghua. Kriging surrogate model and its application to design optimization: a review of recent progress[J]. Acta Aeronautica et Astronautica Sinica,2016,37(11): 3197-3225. (in ChineseHAN Zhonghua. Kriging surrogate model and its application to design optimization: a review of recent progress[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(11): 3197-3225. (in Chinese) [30] 肖立峰,张广泉,张以都. 基于Kriging代理模型的结构形状优化方法[J]. 机械设计,2009,26(7): 57-60. XIAO Lifeng,ZHANG Guangquan,ZHANG Yidu. Optimization method of structural shape based on Kriging surrogate model[J]. Journal of Machine Design,2009,26(7): 57-60. (in ChineseXIAO Lifeng, ZHANG Guangquan, ZHANG Yidu. Optimization method of structural shape based on Kriging surrogate model[J]. Journal of Machine Design, 2009, 26(7): 57-60. (in Chinese) [31] 韩忠华,张瑜,许晨舟,等. 基于代理模型的大型民机机翼气动优化设计[J]. 航空学报,2019,40(1): 150-165. HAN Zhonghua,ZHANG Yu,XU Chenzhou,et al. Aerodynamic optimization design of large civil aircraft wings using surrogate-based model[J]. Acta Aeronautica et Astronautica Sinica,2019,40(1): 150-165. (in ChineseHAN Zhonghua, ZHANG Yu, XU Chenzhou, et al. Aerodynamic optimization design of large civil aircraft wings using surrogate-based model[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(1): 150-165. (in Chinese) [32] GHORANI M M,SOTOUDE HAGHIGHI M H,RIASI A. Entropy generation minimization of a pump running in reverse mode based on surrogate models and NSGA-Ⅱ[J]. International Communications in Heat and Mass Transfer,2020,118: 104898. doi: 10.1016/j.icheatmasstransfer.2020.104898 [33] 朱博文,龚懿,陈再扬,等. 基于Pareto最优解的跨流域调水泵站多目标优化运行研究[J]. 灌溉排水学报,2022,41(2): 131-139. ZHU Bowen,GONG Yi,CHEN Zaiyang,et al. Multi-objective optimization of cross-basin water pump station solved by the Pareto method[J]. Journal of Irrigation and Drainage,2022,41(2): 131-139. (in ChineseZHU Bowen, GONG Yi, CHEN Zaiyang, et al. Multi-objective optimization of cross-basin water pump station solved by the Pareto method[J]. Journal of Irrigation and Drainage, 2022, 41(2): 131-139. (in Chinese) [34] 裴胜玉,周永权. 基于Pareto最优解集的多目标粒子群优化算法[J]. 计算机工程与科学,2010,32(11): 85-88. PEI Shengyu,ZHOU Yongquan. A multi-objective particle swarm algorithm based on the Pareto optimization solution set[J]. Computer Engineering & Science,2010,32(11): 85-88. (in ChinesePEI Shengyu, ZHOU Yongquan. A multi-objective particle swarm algorithm based on the Pareto optimization solution set[J]. Computer Engineering & Science, 2010, 32(11): 85-88. (in Chinese) -
点击查看大图
计量
- 文章访问数: 731
- HTML浏览量: 332
- PDF量: 66
- 被引次数: 0