超临界层流翼型优化设计策略

doi:10.13700/j.bh.1001-5965.2016.0656

北京航空航天大学学报 ›› 2017, Vol. 43 ›› Issue (8): 1616-1624.doi: 10.13700/j.bh.1001-5965.2016.0656

超临界层流翼型优化设计策略

邢宇, 罗东明, 余雄庆

南京航空航天大学飞行器先进设计技术国防重点学科实验室, 南京 210016

收稿日期:2016-08-09 修回日期:2016-10-14 出版日期:2017-08-20 发布日期:2016-11-14
通讯作者: 余雄庆 E-mail:yxq@nuaa.edu.cn
作者简介:邢宇,男,博士研究生。主要研究方向:飞行器多学科设计优化;罗东明,男,博士,讲师,硕士生导师。主要研究方向:飞机总体设计、计算空气动力学;余雄庆,男,博士,教授,博士生导师。主要研究方向:飞行器总体设计、飞行器多学科设计优化。
基金资助:
国家自然科学基金（11432007）

Optimization strategy of supercritical laminar flow airfoil design

XING Yu, LUO Dongming, YU Xiongqing

Key Laboratory of Fundamental Science for National Defense Advanced Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2016-08-09 Revised:2016-10-14 Online:2017-08-20 Published:2016-11-14
Supported by:
National Natural Science Foundation of China (11432007)

摘要/Abstract

摘要： 针对超临界层流翼型设计问题，提出一种两轮优化策略。采用γ-Re_θt转捩模型耦合剪切应力输运（SST）模式的湍流模型对翼型边界层转捩进行预测。翼型几何参数化建模采用形状分类函数转换（CST）方法，设计变量为描述翼型几何特征的参数。第1轮优化的目的是尽量提高层流区域的比例，气动分析模型为基于Kriging模型的代理模型，优化算法为遗传算法，通过优化获得满足约束要求的层流翼型。第2轮优化目的是对第1轮优化获得的翼型进行微调，进一步提高翼型的升阻比，气动分析直接采用CFD程序，优化算法采用基于梯度的优化算法。算例表明，应用本文提出的两轮优化策略，可将超临界翼型NASA SC（2）0412优化设计成超临界层流翼型，翼型的上下表面层流区比例分别达到了55.5%和47.0%，升阻比提高了38.1%。

关键词: 层流, 翼型, 优化, 空气动力学, 代理模型

Abstract: A two-step optimization strategy for the supercritical laminar flow airfoil design is proposed in the paper. The γ-Re_θt transition model coupled with the shear stress transportation (SST) turbulence model is used for prediction of airfoil boundary layer transition. The Class/Shape Transformation (CST) method is used to parameterize airfoil geometry. The parameters in the airfoil geometry model are used as the design variables. The first step of optimization is to increase the ratio of the laminar flow region. A genetic algorithm based on the Kriging surrogate model is employed to obtain the laminar flow airfoil with all constraints satisfied. The second step of optimization is to improve the optimization result of the first step, and to further increase the lift-to-drag ratio of the airfoil. A gradient based optimization is used to search optimal solution. The aerodynamic analysis during the second step optimization is implemented through the CFD code rather than the surrogate model. The example demonstrates that the supercritical airfoil NASA SC(2) 0412 can be optimized into a supercritical laminar flow airfoil by the two-step optimization method, the laminar region ratios on the airfoil upper and lower surface increase by 55.5% and 47.0% respectively, and the lift-to-drag ratio increases by 38.1%.

Key words: laminar flow, airfoil, optimization, aerodynamics, surrogate model

中图分类号:

V221⁺.3

邢宇, 罗东明, 余雄庆. 超临界层流翼型优化设计策略[J]. 北京航空航天大学学报, 2017, 43(8): 1616-1624.

XING Yu, LUO Dongming, YU Xiongqing. Optimization strategy of supercritical laminar flow airfoil design[J]. JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2017, 43(8): 1616-1624.

参考文献

[1] SCHRAUF G.Status and perspectives of laminar flow[J].Aeronautical Journal,2005,109(1102):639-644.
[2] THIBERT J J,RENEAUX J,SCHMITT V.Onera activities on drag reduction[C]//Proceedings of the 14th Congress of ICAS.Bonn:ICAS,1990:1053-1064.
[3] FUJINO M,YOSHIZAKI Y,KAWAMURA Y.Natural-laminar-flow airfoil development for a lightweight business jet[J].Journal of Aircraft,2003,40(4):609-615.
[4] FUJINO M.Design and development of the HondaJet[J].Journal of Aircraft,2005,42(3):755-764.
[5] BRADLEY M K,DRONEY C K.Subsonic ultra green aircraft research:Phase I:Final report:NASA/CR-2011-216847[R].Washington,D.C.:NASA,2011.
[6] BRADLEY M K,DRONEY C K.Subsonic ultra green aircraft research phase Ⅱ:N+4 advanced concept development:NASA/CR-2012-217556[R].Washington,D.C.:NASA,2012.
[7] 乔志德.自然层流超临界翼型的设计研究[J].实验流体力学,1998(4):23-30.QIAO Z D.Design of supercritical airfoils with natural laminar flow[J].Journal of Experiments in Fluid Mechanics,1998(4):23-30(in Chinese).
[8] 杨青真,张仲寅.超临界层流机翼边界层及气动特性分析[J].航空学报,2004,25(5):438-442.YANG Q Z,ZHANG Z Y.Analysis of the boundary layer and aerodynamic characteristics of a supercritical laminar wing[J].Acta Aeronautica et Astronautica Sinica,2004,25(5):438-442(in Chinese).
[9] 孙朋朋,黄章峰.后掠角对后掠机翼边界层稳定性及转捩的影响[J].北京航空航天大学学报,2015,41(7):1313-1321.SUN P P,HUANG Z F. Effect of sweep angle on stability and transition in swept-wing boundary layer[J].Journal of Beijing University of Aeronautics and Astronautics,2015,41(7):1313-1321(in Chinese).
[10] 靖振荣,孙朋朋,黄章峰.小攻角对后掠机翼边界层稳定性及转捩的影响[J].北京航空航天大学学报,2015,41(11):2177-2183.JING Z R,SUN P P,HUANG Z F.Effect of attack angle on stability and transition in swept-wing boundary layer[J].Journal of Beijing University of Aeronautics and Astronautics,2015,41(11):2177-2183(in Chinese).
[11] MENTER F R,LANGTRY R B,LIKKI S R,et al.A correlation-based transition model using local variables-Part Ⅰ:Model formulation[J].Journal of Turbomachinery,2006,128(3):413-422.
[12] MENTER F R.Two-equation eddy-viscosity turbulence models for engineering applications[J].AIAA Journal,1994,32(8):1598-1605.
[13] LANGTRY R B.A correlation based transition model using local variables for unstructured parallelized CFD codes[R].Stuttgart:Stuttgart of University,2006.
[14] 邓磊,乔志德,杨旭东,等.高升阻比自然层流翼型多点/多目标优化设计[J].空气动力学学报,2011,29(3):330-335.DENG L,QIAO Z D,YANG X D,et al.Multi-point/objective optimization design of high lift-to-drag ratio for NLF airfoils[J].Acta Aerodynamica Sinica,2011,29(3):330-335(in Chinese).
[15] HAN Z H,CHEN J,ZHU Z,et al.Aerodynamic design of transonic natural-laminar-flow (NLF) wing via surrogate-based optimization:AIAA-2016-2041[R]. Reston:AIAA,2016.
[16] HAN Z H,DENG J,LIU J,et al.Design of laminar supercritical airfoils based on navier-stokes equations[C]//Proceedings of 28th International Congress of the Aeronautical Sciences. Bonn:ICAS,2012:1-9.
[17] ZHAO K,GAO Z H,HUANG J T.Robust design of natural laminar flow supercritical airfoil by multi-objective evolution method[J].Applied Mathematics and Mechanics,2014,35(2):191-202.
[18] ZHANG Y F,FANG X M,CHEN H X,et al.Supercritical natural laminar flow airfoil optimization for regional aircraft wing design[J].Aerospace Science and Technology,2015,43:152-164.
[19] 马晓永,张彦军,段卓毅,等.自然层流机翼气动外形优化研究[J].空气动力学学报,2015,33(6):812-817.MA X Y,ZHANG Y J,DUAN Z Y,et al.Study of aerodynamic shape optimization for natural laminar wing[J].Acta Aerodynamica Sinica,2015,33(6):812-817(in Chinese).
[20] BARCHE J,BINJON T W,WINTER K G,et al. Experimental data base for computer program assessment:AGARDAR-138[R].London:Technical Editing and Reproduction Ltd.,1979:1-22.
[21] 郑宇宁,邱志平,黄仁,等.二元可变后缘翼型的鲁棒优化设计[J].北京航空航天大学学报,2015,41(5):897-903.ZHENG Y N,QIU Z P,HUANG R,et al.Robust design optimization of a two-dimensional airfoil with deformable trailing edge[J].Journal of Beijing University of Aeronautics and Astronautics,2015,41(5):897-903(in Chinese).
[22] BOGUE D,CRIST N.CST transonic optimization using tran-air++:AIAA-2008-321[R].Reston:AIAA,2008.
[23] 赵童,张宇飞,陈海昕,等.面向三维机翼性能的超临界翼型优化设计方法[J].中国科学:物理学力学天文学,2015,45(10):104708.ZHAO T,ZHANG Y F,CHEN H X,et al.Aerodynamic optimization method of supercritical airfoil geared to the performance of swept and tapered wing[J].Scientia Sinica Physica,Mechanica & Astronomica,2015,45(10):104708(in Chinese).

超临界层流翼型优化设计策略

Optimization strategy of supercritical laminar flow airfoil design

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	王岩, 林彬, 东野广恒, 董颖怀, 赵静楠, 张晓峰. 附件化超声振动工作台设计及有限元优化分析[J]. 北京航空航天大学学报, 2019, 45(8): 1589-1596.
[2]	靳涛, 胡小平, 于保华. 大端接圆柱杆的复合圆锥形变幅杆设计及应用[J]. 北京航空航天大学学报, 2019, 45(8): 1630-1638.
[3]	刘强, 李鹏阳, 许光耀, 王权岱, 杨明顺. 超磁致伸缩超声换能器的磁路优化设计[J]. 北京航空航天大学学报, 2019, 45(8): 1639-1645.
[4]	李红, 张志宾. 基于快速模拟退火的组合聚类算法[J]. 北京航空航天大学学报, 2019, 45(8): 1646-1652.
[5]	郝宝新, 周志成, 曲广吉, 李东泽. 桁架拓扑优化几何稳定性判定法和约束方案比较[J]. 北京航空航天大学学报, 2019, 45(8): 1663-1673.
[6]	王泽坤, 吴明功, 温祥西, 蒋旭瑞, 高阳阳. 基于速度障碍法的飞行冲突解脱与恢复策略[J]. 北京航空航天大学学报, 2019, 45(7): 1294-1302.
[7]	邓昊宇, 王春洁. 三维点阵结构等效热分析与优化方法[J]. 北京航空航天大学学报, 2019, 45(6): 1122-1128.
[8]	史亚云, 郭斌, 刘倩, 白俊强, 杨体浩, 卢磊. 基于能量观点的混合层流优化设计[J]. 北京航空航天大学学报, 2019, 45(6): 1162-1174.
[9]	房涛涛, 李晓星, 肖瑞. 基于双向拉伸的热环境铝合金性能获取和分析[J]. 北京航空航天大学学报, 2019, 45(6): 1195-1202.
[10]	洪杰, 栗天壤, 倪耀宇, 吕春光, 马艳红. 复杂转子系统支点动载荷模型及其优化设计[J]. 北京航空航天大学学报, 2019, 45(5): 847-854.
[11]	吴明功, 蒋旭瑞, 温祥西, 陈彬. 军航飞机流穿越民航航线冲突探测与解脱问题[J]. 北京航空航天大学学报, 2019, 45(5): 863-872.
[12]	罗利龙, 王立凯, 聂小华. 一种面向模块化可重构机翼的分步补偿优化方法[J]. 北京航空航天大学学报, 2019, 45(5): 930-935.
[13]	王少奇, 马东立, 杨穆清, 张良. 高空太阳能无人机三维航迹优化[J]. 北京航空航天大学学报, 2019, 45(5): 936-943.
[14]	吕志峰, 张金生, 王仕成, 赵欣, 李婷. 基于智能优化算法和有限元法的多线圈均匀磁场优化设计[J]. 北京航空航天大学学报, 2019, 45(5): 980-988.
[15]	胡万林, 于剑, 刘宏康, 阎超. 圆弧翼型跨声速流动的动态模态分析[J]. 北京航空航天大学学报, 2019, 45(5): 1026-1032.