超临界自然层流机翼设计及基于TSP技术的边界层转捩风洞试验

doi:10.7527/S1000-6893.2018.22429

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

超临界自然层流机翼设计及基于TSP技术的边界层转捩风洞试验

张彦军¹, 段卓毅¹, 雷武涛¹, 白俊强², 徐家宽²

1. 航空工业第一飞机设计研究院, 西安 710089;
2. 西北工业大学航空学院, 西安 710072

收稿日期:2018-06-07 修回日期:2018-06-25 出版日期:2019-04-15 发布日期:2018-08-16
通讯作者: 张彦军 E-mail:zhangyanjun_fai@163.com

Design of supercritical natural laminar flow wing and its boundary layer transition wind tunnel test based on TSP technique

ZHANG Yanjun¹, DUAN Zhuoyi¹, LEI Wutao¹, BAI Junqiang², XU Jiakuan²

1. AVIC the First Aircraft Institute, Xi'an 710089, China;
2. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received:2018-06-07 Revised:2018-06-25 Online:2019-04-15 Published:2018-08-16

摘要/Abstract

摘要： 为了实现绿色航空节能减排的目标，层流设计技术成为飞行器设计者的研究热点。对于跨声速客机而言，超临界自然层流机翼设计技术将显著减小飞行阻力，提升气动性能，减少燃油消耗和污染物排放。首先，基于高精度边界层转捩预测技术耦合翼型优化设计系统，实现超临界自然层流翼型设计；经过合理的翼型配置，形成超临界自然层流机翼。转捩数值模拟分析结果表明，超临界自然层流机翼的层流流动特性良好。然后，以比例为1：10.4的试验模型在荷兰高速低湍流度风洞进行边界层转捩风洞试验，使用温度敏感材料涂层（TSP）技术拍照获得机翼表面在不同马赫数、雷诺数和迎角工况下的层流-湍流分布。最后，通过超临界自然层流机翼边界层转捩试验结果，探讨了该类型机翼的转捩特性随来流参数的变化规律，总结了超临界自然层流机翼设计的关键因素。此外，该模型也可用来验证边界层转捩预测技术在超临界、高雷诺数工况下的预测精度。

关键词: 自然层流, 超临界机翼, 高雷诺数, 边界层转捩, 温度敏感材料涂层(TSP), 风洞试验

Abstract: To achieve the green aviation goal of energy conservation and emission reduction, laminar flow design technology has become the hot research area for aircraft designers. For transonic airliners, supercritical natural laminar flow wing design technology will significantly reduce the flight drag, improve aerodynamic performance, and decrease fuel consumption and pollutant emissions. Based on the high-precision boundary layer transition prediction technique, the airfoil optimization design system is applied to design the supercritical natural laminar flow airfoils. Then the airfoils are arranged rationally to form the supercritical natural laminar flow wing. Numerical simulations of the supercritical natural laminar flow wing show satisfactory laminar flow characteristics. Then, a model with ratio of 1:10.4 is used to test the boundary layer transition in high speed and low turbulence wind tunnel in Netherland. The Temperature Sensitive Paint (TSP) technique is used to photograph laminar-turbulent area distribution at different Mach numbers, Reynolds numbers and angels of attack. At last, the boundary layer transition characteristics of the supercritical natural laminar flow wing are discussed, and the key factors of the wing design are summarized. In addition, the model can also be used to verify the accuracy of the boundary layer transition prediction technique for supercritical and high Reynolds numbers condition.

Key words: natural laminar flow, supercritical wing, high Reynolds number, boundary layer transition, Temperature Sensitive Paint (TSP), wind tunnel test

中图分类号:

V211

张彦军, 段卓毅, 雷武涛, 白俊强, 徐家宽. 超临界自然层流机翼设计及基于TSP技术的边界层转捩风洞试验[J]. 航空学报, 2019, 40(4): 122429-122429.

ZHANG Yanjun, DUAN Zhuoyi, LEI Wutao, BAI Junqiang, XU Jiakuan. Design of supercritical natural laminar flow wing and its boundary layer transition wind tunnel test based on TSP technique[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(4): 122429-122429.

参考文献

[1] HOLMES B J, OBARA C J. Observations and implications of natural laminar flow on practical airplane surfaces[J]. Journal of Aircraft, 1983, 20(12):993-1006.
[2] KHALID M, JONES D J. A summary of transonic natural laminar flow airfoil development at NAE:NRC No. 31608[R]. Ottawa:NRC, 1990.
[3] LEEJ D, JAMESON A. Natural-laminar-flow airfoil and wing design by adjoint method and automatic transition prediction:AIAA-2009-0897[R]. Reston, VA:AIAA, 2009.
[4] KRUSE M, WUNDERLICH T, HEINRICH L. A conceptual study of a transonic NLF transport aircraft with forward swept wings:AIAA-2012-3208[R]. Reston, VA:AIAA, 2012.
[5] FUJINO M, YOSHIZAKI Y, KAWAMURA Y. Natural-laminar-flow airfoil development for a ligh tweight business jet[J]. Journal of Aircraft, 2003, 40(4):609-615.
[6] FUJINO M. Design and development of the Honda jet[J]. Journal of Aircraft, 2005, 42(3):755-764.
[7] FAUCI R, NICOLÌ A, IMPERATORE B, et al. Wind tunnel tests of a transonic natural laminar flow wing:AIAA-2006-3638[R]. Reston, VA:AIAA, 2006.
[8] CELLA U, QUAGLIARELLA D, DONELLI R, et al. Design and test of the UW-5006 transonic natural-laminar-flow wing[J]. Journal of Aircraft, 2010, 47(3):783-795.
[9] EPPINK J, WLEZIEN R. Data analysis for the NASA/Boeing hybrid laminar flow control crossflow experiment:AIAA-2011-3879[R]. Reston, VA:AIAA, 2011.
[10] 乔志德. 自然层流超临界翼型的设计研究[J]. 流体力学实验与测量, 1998(4):23-30. QIAO Z D. Design of supercritical airfoils with natural laminar flow[J]. Experiments and Measurements in Fluid Mechanics, 1998(4):23-30(in Chinese).
[11] 王菲, 额日其太, 王强, 等. 后掠翼混合层流控制机制的实验[J]. 航空动力学报, 2010, 25(4):918-924. WANG F, E R Q T, WANG Q, et al. The experiment of mechanism in hybrid laminar flow control[J]. Journal of Aerospace Power, 2010, 25(4):918-924(in Chinese).
[12] 孙智伟, 白俊强, 高正红, 等. 现代超临界翼型设计及其风洞试验[J]. 航空学报, 2015, 36(3):804-818. SUN Z W, BAI J Q, GAO Z H, et al. Design and wind tunnel test investigation of the modern supercritical airfoil[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(3):804-818(in Chinese).
[13] HUANG J T, GAOZ H, ZHAO K, et al. Robust design of supercritical wing aerodynamic optimization considering fuselage interfering[J]. Chinese Journal of Aeronautics, 2010, 23(5):523-528.
[14] LI J, GAO Z H, HUANG J T, et al. Robust design of NLF airfoils[J]. Chinese Journal of Aeronautics, 2013, 26(2):309-318.
[15] 乔志德. 翼型的选择与设计[M]//方宝瑞. 飞机气动布局设计. 北京:航空工业出版社, 1997:499-540. QIAO Z D. Design and chosen of the airfoils[M]//FANG B R. Aircraft aerodynamic configuration design. Beijing:Aviation Industry Press, 1997:499-540(in Chinese).
[16] 乔志德, 赵文华, 李育斌, 等. 超临界自然层流冀型NPU-L72513的风洞试验研究[J]. 气动实验与测量控制, 1993, 7(2):40-45. QIAO Z D, ZHAO W H, LI Y B. The transonic wind tunnel test research for the supercritical natural laminar airfoil NPU-L72513[J]. Aerodynamic Experiment and Measurement & Control, 1993, 7(2):40-45(in Chinese).
[17] 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.
[18] HAN Z H, CHEN J, ZHANG K S, et al. Aerodynamic shape optimication of natural-flow wing using surrogate-based approach[J]. AIAA Journal, 2018, 56(7):2579-2593.
[19] 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 Turbomchinery, 2006, 128(3):413-422.
[20] LANGTRY R B, MENTER F R, LIKKI S R, et al. A correlation-based transition model using local variables-part Ⅱ:Test cases and industrial applications[J]. Journal of Turbomachinery, 2006, 128(3):423-434.
[21] LANGTRY R B. A correlation-based transition model using local variables for unstructured parallelized CFDcodes[D]. Stuttgart:Universität Stuttgart, 2006.
[22] LANGTRY R B, MENTER F R. Correlation-based transition modeling for unstructured parallelized computational fluid dynamics codes[J]. AIAA Journal, 2009, 47(12):2894-2906.
[23] SMITHA M O, GAMBERONI N. Transition, pressuregradient, and stability theory:ES-26388[R]. Long Beach:Douglas Aircraft Company, 1956.
[24] VAN INGEN J L. A suggested semi-empirical method for the calculation of the boundary layer transition region:VTH-7[R]. Delft:Delft University of Technology, 1956.
[25] GLEYZES C, COUSTEIX J, BONNET J L. A calculation method of leading edge separation bubbles[M]//CEBECI T. Numerical and physical aspects of aerodynamic flows Ⅱ. New York:Springer-Verlag, 1983:173-192.
[26] DRELA M, GILES M B. Viscous-inviscidanalysis of transonic and low-Reynolds number airfoils[J]. AIAA Journal, 1987, 25(10):1347-1355.
[27] CODER J G, MAUGHMER M D. A CFD-compatible transition model using an amplification factor transport equation:AIAA-2013-0253[R]. Reston, VA:AIAA, 2013.
[28] CODER J G, MAUGHMER M D. Computational fluid dynamics compatible transition modeling using an amplification factor transport equation[J]. AIAA Journal, 2014, 52(11):2506-2512.
[29] MENTERF R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 1994, 32(8):1598-1605.
[30] 徐家宽, 白俊强. 基于边界层相似性解的放大因子输运模型[J]. 航空学报, 2016, 37(4):1103-1113. XU J K, BAI J Q. Amplification factor transport model based on boundary layer similarity solution[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(4):1103-1113(in Chinese).
[31] 尚金奎, 衷洪杰, 赵民, 等. TSP转捩探测技术在民机风洞试验中的应用研究[J]. 空气动力学学报, 2016, 34(3):341-353. SHANG J K, ZHONG H J, ZHAO M, et al. Application of TSP transition detection technique for a civil aircraft[J]. Acta Aerodynamica Sinica, 2016, 34(3):341-353(in Chinese).
[32] ZHU Y D, CHEN X, WU J Z, et al. Aerodynamic heating in transitional hypersonic boundary layers:Role of second-mode instability[J]. Physics of Fluid, 2018, 30(1):011701.
[33] MACK L M. Transition prediction and linear stability theory[C]//In AGARD Laminar-Turbulent Transition 22 p(SEE N78-1431605-34). Paris:AGARD, 1977.
[34] MASELAND J E J, LABAN M, VAN DER VEN H, et al. Development of CFD-based interference models for the DNW-HST transonic wind-tunnel:AIAA-2006-3639[R]. Reston, VA:AIAA, 2006.
[35] ELSENAARA, PHILIPSEN I, VAN DER POEL M. DNW-HST(High-Speed Tunnel) 50-year anniversary:AIAA-2010-0575[R]. Reston, VA:AIAA, 2010.
[36] 尚金奎, 王鹏, 陈柳生, 等. TSP技术在转捩检测中的应用研究[J]. 空气动力学学报, 2015, 33(4):464-469. SHANG J K, WANG P, CHEN L S, et al. Application research of TSP technique in transition detection[J]. Acta Aerodynamica Sinica, 2015, 33(4):464-469(in Chinese).

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

超临界自然层流机翼设计及基于TSP技术的边界层转捩风洞试验

Design of supercritical natural laminar flow wing and its boundary layer transition wind tunnel test based on TSP technique

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]	徐善劼, 吕宏强, 刘中臣, 冷岩, 刘学军. 基于概率模型的声爆试验数据分析[J]. 航空学报, 2023, 44(2): 626269-626269.
[2]	刘中臣, 钱战森, 李雪飞, 冷岩, 郭大鹏. 发动机喷管羽流对近场声爆特性影响的风洞试验技术[J]. 航空学报, 2023, 44(2): 626952-626952.
[3]	束珺, 徐东光, 韩志熔, 李斯, 黄雄. 结冰风洞过冷大水滴试验中混合翼设计[J]. 航空学报, 2023, 44(1): 627182-627182.
[4]	罗凯, 王永海, 汪球, 栗继伟, 李峥, 聂春生, 李铮. 高焓风洞中等离子体激励流动控制试验[J]. 航空学报, 2022, 43(S2): 89-96.
[5]	杜海, 杨乐杰, 李铮, 徐悦, 孙京阳, 王宇航. 多级环量控制技术增升机理及能效分析[J]. 航空学报, 2022, 43(S2): 54-66.
[6]	刘传振, 孟旭飞, 刘荣健, 白鹏. 双后掠乘波体高超声速试验与数值分析[J]. 航空学报, 2022, 43(9): 126015-126015.
[7]	刘强, 涂国华, 罗振兵, 陈坚强, 赵瑞, 袁先旭. 延迟高超声速边界层转捩技术研究进展[J]. 航空学报, 2022, 43(7): 25357-025357.
[8]	刘俊, 罗新福, 王显圣. 前缘形状对空腔模型气动特性影响试验[J]. 航空学报, 2022, 43(7): 125235-125235.
[9]	张桢锴, 贾思嘉, 宋晨, 杨超. 柔性变弯度后缘机翼的风洞试验模型优化设计[J]. 航空学报, 2022, 43(3): 226071-226071.
[10]	侯英昱, 李齐, 季辰, 刘子强. 超声速低频大抖振气动弹性载荷试验[J]. 航空学报, 2022, 43(3): 626454-626454.
[11]	曾开春, 寇西平, 杨兴华, 余立, 查俊. 跨声速风洞试验模型主动减振结构优化设计[J]. 航空学报, 2022, 43(2): 224944-224944.
[12]	李强, 万兵兵, 杨凯, 朱涛. 高超声速尖锥边界层压力脉动和热流脉动特性试验[J]. 航空学报, 2022, 43(2): 124956-124956.
[13]	姜有旭, 李杰, 杨钊. 某层流机翼验证机风洞试验数据修正方法[J]. 航空学报, 2022, 43(11): 526814-526814.
[14]	王猛, 李玉军, 赵荣奂, 衷洪杰. 基于在线加热涂层的宽速域转捩探测技术[J]. 航空学报, 2022, 43(11): 526820-526820.
[15]	姜丽红, 饶寒月, 兰夏毓, 杨体浩, 耿建中, 白俊强. 混合层流机翼气动设计与综合收益影响[J]. 航空学报, 2022, 43(11): 526791-526791.