高雷诺数下跨声速自然层流短舱优化设计

曹凡; 胡骁; 张美芳; 唐智礼

doi:10.13224/j.cnki.jasp.20200459

高雷诺数下跨声速自然层流短舱优化设计

doi: 10.13224/j.cnki.jasp.20200459

南京航空航天大学航空学院非定常空气动力学与流动控制工业和信息化部重点实验室, 南京 210016

基金项目:

国家自然科学基金（NSFC-12032011，11772154）；中央高校基本科研专项资金（NP2020102）；江苏高校优势学科建设工程资助项目（PAPD）

详细信息

作者简介:
曹凡(1990-),男,博士生,主要从事飞行器多学科优化设计研究

中图分类号: V221.3
计量
- 文章访问数: 61
- HTML浏览量: 3
- PDF量: 124
- 被引次数: 0
出版历程
- 收稿日期: 2020-10-30
- 刊出日期: 2021-08-28

Transonic natural laminar flow nacelle optimization design at high Reynolds number

Key Laboratory of Unsteady Aerodynamics and Flow Control of Ministry of Industry and Information Technology, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 为解决高雷诺数下大涵道比发动机自然层流短舱高维优化设计问题，提取短舱3个基准面实现轴对称自然层流优化设计。通过获得较大范围层流区域，从而降低短舱表面摩擦阻力。采用类别形状函数（CST）参数化、γ-Re_θt转捩模型和遗传算法建立自然层流（NLF）短舱自动优化流程。表明通过优化短舱基准面建立三维NLF短舱设计方法的可行性。进而通过CATIA二次开发构建三维非轴对称NLF短舱，解决了基准面优化后大量数据点的高效导入和曲面生成问题。针对设计的非轴对称NLF短舱，进行了设计点附近迎角、侧滑角、来流马赫数以及湍流度的转捩敏感性分析。结果表明：跨声速状态下，迎角增大层流范围减小；来流马赫数增大层流范围扩大；侧滑角和湍流度对层流范围影响很小。
- 自然层流短舱 /
- 气动外形优化 /
- CST参数化 /
- 转捩预测 /
- 转捩敏感性分析
Abstract: To solve the problem of high-dimensional optimization design of laminar flow nacelle with large bypass ratio under high Reynolds number,three datum planes of nacelle were extracted to realize the optimal design of axisymmetric natural laminar flow.A wide range of laminar flow was obtained to reduce the surface friction resistance of the nacelle. An optimization system for the natural laminar flow(NLF) nacelle was established in combination with class and shape transformation (CST) parameterization, γ-Re_θt transition model and the genetic algorithm. It showed the feasibility of establishing a three-dimensional NLF nacelle design method by optimizing the nacelle datum plane.Then, a three-dimensional non -axisymmetric NLF nacelle was constructed through the secondary development of CATIA, which solved the problem of efficiently importing a large number of data points and surface generation after the datum plane optimization. For the designed three-dimensional non-axisymmetric NLF nacelle,a transition sensitivity analysis of the angle of attack,sideslip angle,incoming Mach number,and turbulence intensity near the design point was conducted. The results showed that:under the condition of transonic speed,the laminar flow range decreased with the increase of the angle of attack; the laminar flow range increased with the increase of incoming Mach number; the sideslip angle and turbulence intensity had little effect on the laminar flow range.
- natural laminar flow nacelle /
- aerodynamic shape optimization /
- CST parameterization /
- transition prediction /
- transition sensitivity analysis

HTML

参考文献(27)

[1]	MALIK M R, CROUCH J D, SARIC W S, et al. Application of drag reduction techniques to transport aircraft[M]. New Jersey,US:John Wiley & Sons Limited,2015.
[2]	朱自强,吴宗成,丁举春. 层流流动控制技术及应用[J]. 航空学报,2011,32(5):765-784. ZHU Ziqiang, WU Zongcheng, DING Juchun.Laminar flow control technology and application[J]. Acta Aeronautica et Astronautica Sinica,2011,32(5):765-784.(in Chinese)
[3]	朱自强,鞠胜军,吴宗成. 层流流动主/被动控制技术[J]. 航空学报,2016,37(7):2065-2090. ZHU Ziqiang, JU Shengjun, WU Zongcheng. Laminar flow active/passive control technology[J].Acta Aeronautica et Astronautica Sinica,2016,37(7):2065-2090.(in Chinese)
[4]	YOUNGHANS J L,LAHTI D J.Analytical and experimental studies on natural laminar flow nacelles[R]. AIAA 84-0034,1984.
[5]	RIEDEL H, HORSTMANN K H, RONZHEIMER A, et al.Aerodynamic design of a natural laminar flow nacelle and the design validation by flight testing[J]. Aerospace Science and Technology,1998,2(1):1-12.
[6]	何小龙,白俊强,夏露, 等. 基于EFFD方法的自然层流短舱优化设计[J].航空动力学报,2014,29(10):2311-2320. HE Xiaolong, BAI Junqiang, XIA Lu, et al. Natural laminar flow nacelle optimization design based on EFFD method[J]. Journal of Aerospace Power,2014,29(10):2311-2320.(in Chinese)
[7]	孟晓轩,白俊强,张美红,等. 基于双e^N方法的短舱层流转捩影响因素[J].航空学报,2019,40(11):86-97. MENG Xiaoxuan, BAI Junqiang, ZHANG Meihong, et al. Laminar transition influencing factors of nacelle based on double eN method[J]. Acta Aeronautica et Astronautica Sinica,2019,40(11):86-97.(in Chinese)
[8]	ZHONG Yongjian,LI Songyang.A 3D shape design and optimization method for natural laminar flow nacelle[R]. ASME Paper GT2017-6437,2017.
[9]	WANG S, SUN G, LI C.Natural laminar flow optimization of transonic nacelle based on differential evolution algorithm[J].Journal of Aerospace Engineering,2019,32(4):06019001.1-06019001.10.
[10]	杜玺, 闫海津, 吴宇昂,等. 跨声速自然层流短舱气动设计和风洞试验研究[J].航空科学技术,2019,30(9):63-72. DU Xi,YAN Haijin,WU Yuang,et al.Aerodynamic design and wind tunnel test of a transonic natural laminar flow nacelle[J].Aeronautical Science and Technology, 2019, 30(9):63-72.(in Chinese)
[11]	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[J].航空学报,2015,36(2):449-461. WANG Xun,CAI Jinsheng,QU Kun,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)
[12]	廖炎平,刘莉,龙腾. 几种翼型参数化方法研究[J]. 弹箭与制导学报,2011,31(3):160-164. LIAO Yanping, LIU Li, LONG Teng. The research on some parameterized methods for airfoil[J].Journal of Projectiles,Rockets,Missiles and Guidance,2011,31(3):160-164. (in Chinese)
[13]	KULFAN B M. Recent extensions and applications of the "CST" universal parametric geometry representation method[J].The Aeronautical Journal,2010,114(1153):157-176.
[14]	KULFAN B M.Universal parametric geometry representation method[J].Journal of Aircraft,2008,45(1):142-158.
[15]	宋文萍,吴猛猛,朱震,等. 面向层流减阻设计的转捩预测方法研究[J].空气动力学学报,2018,36(2):213-228. SONG Wenping,WU Mengmeng,ZHU Zhen,et al.Transition prediction methods towards significant drag reduction via laminar flow technology[J]. Acta Aerodynamica Sinica, 2018,36(2):213-228.(in Chinese)
[16]	SARIC W S. Physical description of boundary-layer transition:experimental evidence[R].AGARD-CP-793,1994.
[17]	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.
[18]	乔磊,白俊强,华俊,等.γ-Re_θt转捩模型的改进和验证[J]. 航空动力学报,2015,30(10):2488-2497. QIAO Lei,BAI Junqiang,HUA Jun, et al.Improvement and verification of γ-Re_θt transition model[J]. Journal of Aerospace Power,2015,30(10):2488-2497.(in Chinese)
[19]	韩忠华,王绍楠,韩莉,等. 一种基于动模态分解的翼型流动转捩预测新方法[J].航空学报,2017,38(1):35-51. HAN Zhonghua, WANG Shaonan, HAN Li, et al. A novel method for automatic transition prediction of flows overairfoils based on dynamic mode decomposition[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(1):35-51.(in Chinese)
[20]	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.
[21]	SOMERS D M.Design and experimental results for a natural laminar flow airfoil for general aviation applications[R]. NASA Technical Paper 1861,1981.
[22]	LEE J,JAMESON A.Natural laminar flow airfoil and wing design by adjoint method and automatic transition prediction[R].AIAA-2009-3514,2009.
[23]	TINOCO E N,BRODERSEN O P,KEYE S,et al.Summary data from the sixth AIAA CFD drag prediction workshop:CRM cases[J].Journal of Aircraft,2018,55(4):1352-1379.
[24]	BEASLEY D,BULL D R,MARTIN R R.An overview of genetic algorithms:Part 1 fundamentals[EB/OL].[2020-10-08]. https://sci2s.ugr.es/sites/default/files/files/linksInterest/Tutorials/GA1.pdf.
[25]	HILL G A,KANDIL O A,HAHN A S.Aerodynamic investigations of an advanced over-the-wing nacelle transport aircraft configuration[J].Journal of Aircraft,2009,46(1):25-35.
[26]	闫海津,杜玺. 一种可变流量系数的通气短舱匹配方法[J]. 航空学报,2018,39(12):124-132. YAN Haijin, DU Xi. A matching method for variable mass flow ratio for through-flow nacelle[J]. Acta Aeronautica et Astronautica Sinica,2018,39(12):124-132.(in Chinese)
[27]	周桂生,陆文龙.CATIA二次开发技术研究与应用[J].机械设计与制造,2010,1(1):81-83. ZHOU Guisheng, LU Wenlong.Research and application of CATIA secondary development technology[J]. Machinery Design and Manufacture,2010,1(1):81-83.(in Chinese)