Design and verification of high-lift configuration of civil aircraft standard model CAE-AVM-HL

ZHONG Min; HUA Jun; WANG Hao; BAI Junqiang

doi:10.7638/kqdlxxb-2022.0021

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Design and verification of high-lift configuration of civil aircraft standard model CAE-AVM-HL

更新时间：2026-05-28

- Design and verification of high-lift configuration of civil aircraft standard model CAE-AVM-HL
- Vol. 40, Issue 4, Pages: 158-167(2022)
- 作者机构：
  
  1. 中国航空研究院,北京,100012
  2. 西北工业大学,西安,710072
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0021
  CLC： V211.4
- Published：2022
- 稿件说明：
移动端阅览
钟敏, 华俊, 王浩, 等. 民机标模高升力构型CAE-AVM-HL设计及验证[J]. 空气动力学学报, 2022, 40(4): 158−167.

ZHONG Min, HUA Jun, WANG Hao, et al. Design and verification of high-lift configuration of civil aircraft standard model CAE-AVM-HL[J]. 2022, 40(4): 158-167.
钟敏, 华俊, 王浩, 等. 民机标模高升力构型CAE-AVM-HL设计及验证[J]. 空气动力学学报, 2022, 40(4): 158−167. DOI： 10.7638/kqdlxxb-2022.0021

ZHONG Min, HUA Jun, WANG Hao, et al. Design and verification of high-lift configuration of civil aircraft standard model CAE-AVM-HL[J]. 2022, 40(4): 158-167. DOI： 10.7638/kqdlxxb-2022.0021.

摘要

气动标模高升力构型可用于起降状态复杂流动机理研究、CFD软件验证、低速风洞试验能力建设及增升系统噪声测试。民机气动标模高升力构型CAE-AVM-HL设计过程中采用基于代理模型的数值优化方法，优化流程包含样本建立、参数化几何外形、代理模型建立、遗传算法寻优。机翼增升装置形式为“前缘连续变弯下垂 + 前缘缝翼 + 后缘单缝富勒襟翼”。该民机气动标模高升力构型风洞测试模型在德国Deharde公司完成加工，在德荷大型低速风洞DNW-LLF完成风洞测试，试验马赫数0.2，雷诺数3×10

，测试内容包括测力、测压、测机翼和襟翼变形、转捩效应，以及丝线、油流、PIV试验等。针对前缘变弯下垂和前缘缝翼交界处的流动干扰现象，提出了抗流动分离的设计方案，CFD计算结果和风洞油流试验结果均显示设计方案缓解了前缘变弯下垂和前缘缝翼间的流动干扰。该构型最终风洞测量所得最大升力系数2.56，失速迎角19°，满足设计要求。

Abstract

The high-lift configuration of aerodynamic standard model can be used in various aspects

such as complex flow mechanism study

CFD software verification

low-speed wind tunnel capability research and aero-acoustic test. In the design process of the high-lift configuration of the civil aircraft aerodynamic standard model CAE-AVM-HL

numerical optimization based on the surrogate model is adopted. The optimization process includes sample establishment

geometry parameterization

surrogate model establishment and genetic algorithm optimization. The final form of the high-lift wing is featured with a variable camber droop-nose leading edge

a leading-edge slat and a single slot trailing-edge flap. The wind tunnel test model of civil aircraft aerodynamic standard model with high lift configuration CAE-AVM-HL was processed by Deharde company in Germany

and was tested in the German-Dutch large low-speed wind tunnel DNW-LLF at Mach number 0.2 and Reynolds number 3 million. The wind tunnel test includes force/pressure/deformation measurement

transition trip effect

silk tuft/oil flow

PIV measurement

etc. In view of the influence of the flow interaction between the droop-nose leading edge and the leading-edge slat

an anti-flow separation design scheme is proposed. Both CFD calculation and wind tunnel test show that the anti-flow separation design scheme alleviates the flow interference. The final measured maximum lift coefficient of the configuration is 2.56 and the stall angle of attack is 19°

which meet the design requirements.

关键词

Keywords

references

ZHU Z Q, CHEN Y C, WU Z C, et al. Numerical simulation of high lift system configuration[J]. Acta Aeronautica et Astronautica Sinica, 2005, 26(3): 257-262. (in Chinese)

LAVY D W, VASSBERG J C, WAHLS RA, et al. Summary of data from the first AIAA CFD drag predictioon workshop[C ] //40nd AIAA Aerospace Sciences Meeting, AIAA 2002-0841, 2002. https://ntrs.nasa.gov/api/citations/20030007848/downloads/20030007848.pdf

LAFLIN K, BRODERSEN O, RAKOWITZ M, et al. Summary of data from the second AIAA CFD drag prediction workshop (invited)[C]//42nd AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virginia: AIAA, AIAA 2004-555, 2004. doi: 10.2514/6.2004-555

VASSBERG J C, TINOCO E N, MANI M, et al. Abridged summary of the third AIAA computational fluid dynamics drag prediction workshop[J]. Journal of Aircraft, 2008, 45(3): 781-798. DOI:10.2514/1.30572

VASSBERG J C, TINOCO E N, MANI M R, et al. Summary of the fourth AIAA computational fluid dynamics drag prediction workshop[J]. Journal of Aircraft, 2014, 51(4): 1070-1089. DOI:10.2514/1.c032418

LEVY D W, LAFLIN K R, TINOCO E N, et al. Summary of data from the fifth computational fluid dynamics drag prediction workshop[J]. Journal of Aircraft, 2014, 51(4): 1194-1213. DOI:10.2514/1.c032389

TINOCO E N, BRODERSEN O, KEYE S, et al. Summary of data from the sixth AIAA CFD drag prediction workshop: CRM cases 2 to 5[C]//55th AIAA Aerospace Sciences Meeting, Grapevine, Texas. Reston, Virginia: AIAA, AIAA-2017-1208, 2017. doi: 10.2514/6.2017-1208

SLOTNICK J, HANNON J, CHAFFIN M. Overview of the First AIAA CFD high lift prediction workshop[C]//49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Orlando, Florida. Reston, Virginia: AIAA, 2011. AIAA-2011-0862. doi: 10.2514/6.2011-862

RUMSEY C L, SLOTNICK J P. Overview and summary of the second AIAA high lift prediction workshop[C]//52nd Aerospace Sciences Meeting, National Harbor, Maryland. Reston, Virginia: AIAA, AIAA-2014-0747, 2014. doi: 10.2514/6.2014-0747

LIN J C, PACK MELTON L G, VIKEN S, et al. High lift common research model for wind tunnel testing: an active flow control perspective[C]//55th AIAA Aerospace Sciences Meeting, Grapevine, Texas. Reston, Virginia: AIAA, AIAA 2017-0319, 2017. doi: 10.2514/6.2017-0319

LACY D S, SCLAFANI A J. Development of the high lift common research model (HL-CRM): a representative high lift configuration for transonic transports[C]//54th AIAA Aerospace Sciences Meeting, San Diego, California, USA. Reston, Virginia: AIAA, AIAA 2016-0308, 2016. doi: 10.2514/6.2016-0308

钟敏, 华俊, 王钢林, 等. 面向高亚音速远程飞机的CFD验证与风洞试验相关性研究[C]//第八届中国航空学会青年科技论坛论文集, 2018.

HUA J, ZHENG S, ZHONG M, et al. Recent development of a CFD-wind tunnel correlation study based on CAE-AVM investigation[J]. Chinese Journal of Aeronautics, 2018, 31(3): 419-428. DOI:10.1016/j.cja.2018.01.017

ZHONG M, ZHENG S, WANG G L, et al. Correlation analysis of combined and separated effects of wing deformation and support system in the CAE-AVM study[J]. Chinese Journal of Aeronautics, 2018, 31(3): 429-438. DOI:10.1016/j.cja.2018.01.015

GEBBINK R, WANG G L, ZHONG M. High-speed wind tunnel test of the CAE aerodynamic validation model[J]. Chinese Journal of Aeronautics, 2018, 31(3): 439-447. DOI:10.1016/j.cja.2018.01.010

HUA J, ZHENG S, ZHONG M, et al. Design and verification study of an aerodynamic validation model[C ] //7th Asia-Pacific International Symposium on Aerospace Technology, 2015. http://cae-dnw-workshop.dnw.aero/uploads/files/e151125aFinal00167-APISAT-2015-CAE-HUA.pdf

ZHONG M, WANG G L, HUA J. Study of model deformation and sting interference to the aerodynamic estimations of the CAE-AVM model[C ] //30 th Congress of the International Council of the Aeronautical Sciences, DCC, Daejeon, Korea, ICAS-2016-2.7. 2, 2016. https://www.icas.org/ICAS_ARCHIVE/ICAS2016/data/papers/2016_0405_paper.pdf

GEBBINK R T, WANG G L, ZHONG M. High-speed wind tunnel test of the CAE-AVM for CFD validation purposes[C]//55th AIAA Aerospace Sciences Meeting, Grapevine, Texas, AIAA 2017-0332, 2017. doi: 10.2514/6.2017-0332

ZHONG M, HUA J, SUN X S, et al. Data correlation between aerodynamic validation model and CFD-wind tunnel[J]. Aeronautical Science Technology, 2020, 31(1): 1-16. (in Chinese)

《飞机设计手册》总编委会, 编. 飞机设计手册, 第5册: 民用飞机总体设计[R]. 程不时, 分册主编. 北京: 航空工业出版社, 2005.

艾德·奥波特, 著. 运输类飞机的空气动力设计[M]. 顾诵芬, 吴兴世, 杨新军, 译. 上海: 上海交通大学出版社, 2010.

WANG H J, LUO W, ZHANG R. The analysis of noise features for multi-element airfoil based on slat configuration parameters[J]. Advances in Aeronautical Science and Engineering, 2018, 9(1): 53-61. (in Chinese)

GUO T B, BAI J Q, LI L, et al. The morphing trailing-edge wing optimization design of the civil aircraft[J]. SCIENTIA SINICA Technologica, 2018, 48(1): 55-66. (in Chinese)

LI X F, ZHANG M J, WANG W J, et al. Research on variable camber wing technology development[J]. Aeronautical Science Technology, 2020, 31(2): 12-24. (in Chinese)

YANG Y, WANG Z G, LYU S S. Comparative study of two lay-up sequence dispositions for flexible skin design of morphing leading edge[J]. Chinese Journal of Aeronautics, 2021, 34(7): 271-278. DOI:10.1016/j.cja.2020.03.035

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