超声速翼型气动优化设计

doi:10.7527/S1000-6893.2015.0118

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

超声速翼型气动优化设计

曹长强¹, 蔡晋生¹, 段焰辉²

1. 西北工业大学航空学院, 西安 710072;
2. 中国空气动力研究与发展中心计算空气动力学研究所, 绵阳 621000

收稿日期:2015-02-06 修回日期:2015-05-04 出版日期:2015-12-15 发布日期:2015-05-05
通讯作者: 蔡晋生,Tel.:029-88495381,E-mail:caijsh@nwpu.edu.cn E-mail:caijsh@nwpu.edu.cn
作者简介:曹长强,男,博士研究生。主要研究方向:气动优化设计,降阶模型,E-mail:caoch0501@163.com;蔡晋生,男,博士,教授,博士生导师。主要研究方向:飞行器气动布局设计,计算流体力学,复杂流动控制。Tel:029-88495381,E-mail:caijsh@nwpu.edu.cn;段焰辉,男,博士。主要研究方向:计算流体力学,优化设计,E-mail:duanyanhui@foxmail.com

Aerodynamic design optimization of supersonic airfoils

CAO Changqiang¹, CAI Jinsheng¹, DUAN Yanhui²

1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. Computational Aerodynamics Institute, China Aerodynamics Research and Development Centre, Mianyang 621000, China

Received:2015-02-06 Revised:2015-05-04 Online:2015-12-15 Published:2015-05-05

摘要/Abstract

摘要：

首先分析了几何外形和相对厚度对超声速翼型气动特性的影响。基于遗传算法(GA)和气动力快速工程算法,对于相对厚度为3.5%的多边形翼型进行优化设计,多边形翼型的优化外形趋于四边形,最大厚度点后移到翼型弦线的60%左右,随着迎角或者马赫数增大下翼面会变薄,上翼面变厚,最大厚度点相应稍有后移。对于相对厚度为4%的双圆弧翼型,采用两步优化设计方法,第1步优化结合基于B样条的类别形状函数变换(CST)参数化方法与小波分解方法,实现几何外形的局部控制与光顺处理,并且采用本征正交分解(POD)代理模型降低优化过程中流场计算的工作量;第2步优化采用基于Navier-Stokes方程的最速下降法(SDA),修正第1步优化中代理模型和小波光顺引入的误差;优化设计得到的翼型近似为四边形,其相对厚度最大点后移到翼型弦线的60%~65%处,升阻比可以提高7%。

关键词: 超声速翼型, 优化设计, 代理模型, 参数化, 小波分解

Abstract:

Firstly, the aerodynamic performance of supersonic airfoils with different geometric shapes and relative thickness is compared and analyzed. Secondly, design optimization is implemented for the polygonal airfoils of 3.5% relative thickness by combining genetic algorithm (GA) and rapid aerodynamic engineering algorithm. The design optimization process makes the polygonal airfoil approach to be a quadrilateral in shape with the maximum thickness location moving to about 60% of the chord. As the angle of attack or Mach number increases, the lower surface will become thinner, the upper surface will become thicker and the maximum thickness location will move backward slightly. Furthermore, for the biconvex airfoil of 4% relative thickness, a two-step design optimization method is used. In the first step, class and shape transformation (CST) based on B-spline basis function is used combined with wavelet decomposition to enhance the local control and fairing abilities. A surrogate model based on proper orthogonal decomposition (POD) is chosen to reduce the computational workload. The second step optimization employs the steepest decent algorithm (SDA) based on the Navier-Stokes equations to correct the errors caused by POD method and wavelet decomposition in the first step optimization. The optimized airfoil approximates to be a quadrilateral in shape, with the maximum thickness location moving to 60%-65% of the chord and lift-to-drag ratio increasing by 7%.

Key words: supersonic airfoils, design optimization, surrogate model, parameterization, wavelet decomposition

中图分类号:

V211.41⁺2

曹长强, 蔡晋生, 段焰辉. 超声速翼型气动优化设计[J]. 航空学报, 2015, 36(12): 3774-3784.

CAO Changqiang, CAI Jinsheng, DUAN Yanhui. Aerodynamic design optimization of supersonic airfoils[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(12): 3774-3784.

参考文献

[1] Ruffin S M, Gupta A, Marshall D. Supersonic channel airfoils for reduced drag[J]. AIAA Journal, 2000, 38(3):480-486.
[2] Lobbia M A, Suzuki K. Multidisciplinary design optimization of hypersonic, AIAA-2014-2359[R]. Reston:AIAA, 2014.
[3] Lobbia M A, Suzuki K. Experimental investigation of a Mach 3.5 waverider designed using computational fluid dynamics[J]. AIAA Journal, 2015, 53(6):1590-1601.
[4] Shapiro A H. The dynamics and thermodynamics of compressible fluid flow[M]. New York:The Ronald Press Company, 1954:745-770.
[5] Yan C, Xie L, Li Y X, et al. Optimum method and inverse method for aerodynamic design of airfoil[J]. Acta Aerodynamic Sinica, 1999, 17(1):60-67(in Chinese).阎超,谢磊,李云晓,等.翼型的气动最优化设计方法和反设计方法[J].空气动力学学报, 1999, 17(1):60-67.
[6] Liu H, Zhu Z Q, Yu R X, et al. Optimization design of adaptive airfoil's aerodynamic shape[J]. Acta Aeronautica et Astronautica Sinica, 2002, 23(4):289-293(in Chinese).刘航,朱自强,吁日新,等.自适应翼型的气动外形优化设计[J].航空学报, 2002, 23(4):289-293.
[7] Duan Y H. Research on methods of aerodynamic shape optimization for hypersonic vehicles[D]. Xi'an:Northwestern Polytechnical University, 2013(in Chinese).段焰辉.高超声速飞行器气动外形优化设计方法研究[D].西安:西北工业大学, 2013.
[8] Hao J A, Jiang C W, Gao Z X, et al. Aerodynamic engineering prediction methods for winged reentry vehicles[J]. Chinese Space Science and Technology, 2014(3):38-45(in Chinese).郝佳傲,蒋崇文,高振勋,等.有翼再入飞行器的超/高超声速气动力工程方法[J].中国空间科学技术, 2014(3):38-45.
[9] Gao Q, Zhang W M, Chen Y W. Rapid calculation of aerodynamic characteristics of new supersonic and hypersonic aircrafts with inlets[J]. Journal of Astronautics, 2008, 29(2):494-498(in Chinese).高清,张卫民,陈英文.新一代超/高超声速带进气道飞行器气动力特性快速计算[J].宇航学报, 2008, 29(2):494-498.
[10] Liu C Z, Duan Y H, Cai J S. Aerodynamic shape optimization based on multi-block class and shape transformation[J]. Journal of Astronautics, 2014, 35(2):137-143(in Chinese).刘传振,段焰辉,蔡晋生.气动外形优化中的分块类别形状函数法研究[J].宇航学报, 2014, 35(2):137-143.
[11] Holmes P, Lumley J, Berkooz G. Turbulence, coherent structures, dynamical systems and symmetry[M]. Cambridge:Cambridge University Press, 1996:86-113.
[12] Sirovich L, Kirby M. Turbulence and the dynamics of coherent structures. I:Coherent structures[J]. Quarterly of Applied Mathematics, 1987, 45(3):561-571.
[13] Everson R, Sirovich L. Karhunen-Loeve procedure for gappy data[J]. Journal of the Optical Society of America A, 1995, 12(8):1657-1664.
[14] Bui-Thanh T, Damodaran M, Willcox K. Aerodynamic data reconstruction and inverse design using proper orthogonal decomposition[J]. AIAA Journal, 2004, 42(8):1505-1516.
[15] Duan Y H, Cai J S, Li Y Z. Gappy proper orthogonal decomposition-based two-step optimization for airfoil design[J]. AIAA Journal, 2012, 50(4):968-971.
[16] Bai J Q, Qiu Y S, Hua J. Improved airfoil inverse design method based on Gappy POD[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(4):762-771(in Chinese).白俊强,邱亚松,华俊.改进型Gappy POD翼型反设计方法[J].航空学报, 2013, 34(4):762-771.
[17] Wang X, Cai J S, Qu K, et al. Airfoil optimization based on improved CST parametric method and transition model[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(2):449-461(in Chinese).王迅,蔡晋生,屈崑,等.基于改进CST参数化方法和转捩模型的翼型优化设计研究[J].航空学报, 2015:36(2):449-461.
[18] Zhu F, Qin N. Intuitive class/shape function parameterization for airfoils[J]. AIAA Journal, 2014, 52(1):17-25.
[19] Kulfan B M, Bussoletti J E. "Fundamental" parametric geometry representation for aircraft component shapes, AIAA-2006-6948[R]. Reston:AIAA, 2006.
[20] Kulfan B M. Recent extensions and applications of the "CST" universal parametric geometry representation method, AIAA-2007-7709[R]. Reston:AIAA, 2007.
[21] Kulfan B M. A universal parametric geometry representation method-"CST", AIAA-2007-0062[R]. Reston:AIAA, 2007.
[22] Guan X H, Li Z K, Song B F. A study on CST aerodynamic shape parameterization method[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(4):625-633(in Chinese).关晓辉,李占科,宋笔锋. CST气动外形参数化方法研究[J].航空学报, 2012, 33(4):625-633.
[23] Straathof M H, van Tooren M J L. Extension to the class-shape-transformation method based on B-splines[J]. AIAA Journal, 2011, 49(4):780-790.
[24] Finkelstein A, Salesin D H. Multiresolution curves[C]//Proceedings of the 21st Annual Conference on Computer Graphics and Interactive Techniques, 1994.
[25] Mu G W, Zang T, Zhao G. Wavelet-based local fairing algorithm for B-spline curves[J]. Journal of Engineering Graphics, 2006, 27(2):84-89(in Chinese).穆国旺,臧婷,赵罡.基于小波的B样条曲线局部光顺算法[J].工程图学学报, 2006, 27(2):84-89.
[26] Piegl L, Tiller W. The nurbs book[M]. Zhao G, Mu G W, Wang L Z, translated. Beijing:Tsinghua University Press, 2010:34-36(in Chinese). Piegl L, Tiller W.非均匀有理B样条[M].赵罡,穆国旺,王拉柱,译.北京:清华大学出版社, 2010:34-36.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

超声速翼型气动优化设计

Aerodynamic design optimization of supersonic airfoils

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]	崔壮壮, 原昕, 赵国庆, 井思梦, 招启军. 共轴刚性旋翼高速直升机前飞性能操纵策略影响[J]. 航空学报, 2024, 45(9): 529256-529256.
[2]	柳家齐, 陈荣钱, 楼锦华, 韩旭, 吴昊, 尤延铖. 基于深度学习的高速直升机旋翼翼型气动优化设计[J]. 航空学报, 2024, 45(9): 529828-529828.
[3]	王梓旭, 李攀, 鲁可, 朱振华, 陈仁良. 共轴刚性旋翼高速直升机配平策略优化设计[J]. 航空学报, 2024, 45(9): 529069-529069.
[4]	贾文斌, 方磊, 张根, 史剑, 何泽侃, 宣海军. CNT树脂基复合材料断裂韧性的优化设计[J]. 航空学报, 2024, 45(7): 428971-428971.
[5]	骆燕燕, 杨硕, 潘晓松, 赵绪怀, 张莉. 航空用高速连接器信号反射抑制与优化设计[J]. 航空学报, 2024, 45(7): 328937-328937.
[6]	戴今钊, 陈海昕. 流场波系引导的三维消波翼优化设计方法[J]. 航空学报, 2024, 45(6): 628942-628942.
[7]	陈树生, 贾苜梁, 刘衍旭, 高正红, 向星皓. 变体飞行器变形方式及气动布局设计关键技术研究进展[J]. 航空学报, 2024, 45(6): 629595-629595.
[8]	陈树生, 冯聪, 张兆康, 赵轲, 张新洋, 高正红. 基于全局/梯度优化方法的宽速域乘波-机翼布局气动设计[J]. 航空学报, 2024, 45(6): 629596-629596.
[9]	李玉涵, 杨宝玉, 吴亦农, 张强, 唐晓. 卫星光机载荷热模型参数高效修正方法研究进展[J]. 航空学报, 2024, 45(6): 628814-628814.
[10]	万冰, 陈军, 白菡尘. 基于等效热力过程的宽域冲压全流道性能设计方法[J]. 航空学报, 2024, 45(4): 128757-128757.
[11]	王科雷, 周洲, 郭佳豪, 李明浩. 分布式动力翼前飞状态动力/气动耦合特性[J]. 航空学报, 2024, 45(2): 128643-128643.
[12]	余婧, 蒋安林, 刘亮, 吴晓军, 桂业伟, 刘深深. 基于PCA降维的气动外形参数化方法[J]. 航空学报, 2024, 45(10): 129125-129125.
[13]	王四季, 张羽薇, 黄开明, 吕彪, 赵海凤, 王虎, 廖明夫. 基于改进粒子群算法的直升机动力涡轮转子系统优化方法[J]. 航空学报, 2024, 45(1): 228608-228608.
[14]	崔凯鑫, 段广仁. 基于干扰观测器的一类组合航天器高阶全驱抗干扰控制[J]. 航空学报, 2024, 45(1): 628892-628892.
[15]	杨倩, 郑皓冉, 程显达, 董威. 基于引气控制的热气防冰优化设计方法[J]. 航空学报, 2023, 44(S2): 729285-729285.