CHN-T2标模跨声速抖振特性及雷诺数效应研究

豆子皓; 吴军强; 高传强; 张伟伟

doi:10.7638/kqdlxxb-2023.0035

欢迎来到能源电力期刊网！

English Version 期刊登录

您当前的位置：

首页 >

文章列表页 >

CHN-T2标模跨声速抖振特性及雷诺数效应研究

高雷诺数复杂流动问题研究 | 更新时间：2026-07-27

- CHN-T2标模跨声速抖振特性及雷诺数效应研究
- Transonic buffet characteristics and Reynolds number effects of CHN-T2 standard model
- 空气动力学学报 2024年42卷第8期页码：93-107
- 作者机构：
  
  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,绵阳,621000
- 作者简介：
  
  豆子皓（1996—），男，陕西咸阳人，博士生，研究方向：气动弹性力学. E-mail：douzhbean@foxmail.com
  高传强*，教授，研究方向：气动弹性力学，流动控制. E-mail：gaocq@nwpu.edu.cn
- 基金信息：
- DOI：10.7638/kqdlxxb-2023.0035
  中图分类号： V211.78
- 纸质出版：2024
- 稿件说明：
移动端阅览
豆子皓, 吴军强, 高传强, 等. CHN-T2标模跨声速抖振特性及雷诺数效应研究[J]. 空气动力学学报, 2024, 42(8): 93−107.

DOU Zihao, WU Junqiang, GAO Chuanqiang, et al. Transonic buffet characteristics and Reynolds number effects of CHN-T2 standard model[J]. 2024, 42(8): 93-107.
豆子皓, 吴军强, 高传强, 等. CHN-T2标模跨声速抖振特性及雷诺数效应研究[J]. 空气动力学学报, 2024, 42(8): 93−107. DOI： 10.7638/kqdlxxb-2023.0035

DOU Zihao, WU Junqiang, GAO Chuanqiang, et al. Transonic buffet characteristics and Reynolds number effects of CHN-T2 standard model[J]. 2024, 42(8): 93-107. DOI： 10.7638/kqdlxxb-2023.0035.

摘要

新一代客机具有较高的巡航速度，跨声速抖振和雷诺数效应研究是其气动设计中的关键一环。采用基于

SST湍流模型耦合延迟脱体涡模拟技术的高精度数值模拟方法，针对CHN-T2宽体客机气动标模开展了相关研究，并基于非定常计算明确了CHN-T2标模在巡航马赫数

= 0.85、飞行雷诺数

= 5×10

工况下的抖振始发迎角约为4.4°。结果表明，CHN-T2标模机翼在抖振超临界迎角下同时存在由激波弦向振荡主导的低频成分（

0.0297

）和由翼根尾缘复杂高压区主导的高频成分（

= 0.314）。在雷诺数效应方面，从风洞实验雷诺数（

= 5×10

）到飞行雷诺数（

= 5×10

）巡航状态下，CHN-T2机翼激波位置后移约10%当地弦长，附面层高度降低1/2 ～ 1/10，进而引发升/阻力系数发生明显变化。升力系数和摩阻系数的雷诺数效应不随迎角改变，而压阻系数的雷诺数效应与迎角线性相关。同时，雷诺数变化会显著影响抖振非定常流场求解，过低的模拟雷诺数会导致激波振荡消失。

Abstract

The next-generation passenger aircraft feature higher cruise speeds

rendering transonic buffet and Reynolds number effects pivotal in their aerodynamic design. This paper employs the high-precision delayed detached eddy simulation

based on the

k-ω

SST turbulence model

to investigate the aerodynamic characteristics

of the CHN-T2 model for wide-body aircraft. Unsteady simulations demonstrate that

for a cruise Mach number of 0.85 and a Reynolds number of

= 5×10

the critical angle of attack at which the transonic buffet manifests is 4.4°. Large-scale separation around the wing root trailing edge serves as an indicator for the presence of the transonic buffet of CHN-T2

which exhibits the low-frequency (

0.0297

) shock oscillation and high-frequency (

= 0.314) fluctuations in the high-pressure region near the trailing edge of the wing root. Regarding the Reynolds number effects

as the Reynolds number increases from

= 5×10

to 5×10

the shock wave position on the CHN-T2 wing shifts aft by approximately 10% of the local chord length

and the boundary layer thickness decreases by 10% to 50%

resulting in considerable variation in the aerodynamic coefficients. It is further revealed that the Reynolds number effect on the lift and friction drag coefficients remains unchanged regardless of the angle of attack

whereas that on the pressure drag coefficient is linearly correlated with the angle of attack. Concurrently

the variation in the Reynolds number significantly affects the unsteady flow field of transonic buffet

with excessively low Reynolds numbers potentially leading to the disappearance of shock wave oscillations. An increase in the Reynolds number will significantly enhance the shock oscillation intensity but barely affect the high-frequency fluctuations at the wing root trailing edge.

关键词

Keywords

references

ZHANG W W, GAO C Q, YE Z Y . The complexity and mechanism of transonic aeroelastic problems[J ] . Chinese Science Bulletin, 2018 , 63 ( 12 ): 1095 − 1110 (in Chinese).

WANG Y L, GAO C, WANG N . On the influence of Reynolds number on airfoil buffet characteristics[J ] . Journal of Experimental Mechanics, 2016 , 31 ( 3 ): 386 − 392 (in Chinese).

LIU H Y, ZHOU Z, YU Y G, et al . Design of a standard aerodynamic model CHN-T2 for wide-body aircraft[J ] . Acta Aerodynamica Sinica, 2023 , 41 ( 10 ): 15 − 29 (in Chinese).

BÉRARD A, ISIKVEREN A T . Conceptual design prediction of the buffet envelope of transport aircraft[J ] . Journal of Aircraft, 2009 , 46 ( 5 ): 1593 − 1606 .

LEE B H K, MURTY H, JIANG H . Role of Kutta waves on oscillatory shock motion on an airfoil[J ] . AIAA Journal, 1994 , 32 ( 4 ): 789 − 796 .

WANG Z H, LI G, LIU D W, et al . Buffeting boundary prediction method of supercritical wing using LSTM[J ] . Acta Aerodynamica Sinica, 2023 , 42 ( 6 ): 56 − 65 (in Chinese).

DOU Z H, GAO C Q, ZHANG W W, et al . Nonlinear aeroelastic prediction in transonic buffeting flow by deep neural network[J ] . AIAA Journal, 2023 , 61 ( 6 ): 2412 − 2429 .

DONG S H, SHI A M, YE Z Y, et al . CFD computation and POD analysis for transonic buffet on a supercritical airfoil[J ] . Acta Aerodynamica Sinica, 2015 , 33 ( 4 ): 481 − 487 (in Chinese).

REN K, GAO C Q, ZHANG W W . Model-free adaptive control of shock buffet flow over an airfoil[J ] . Acta Aerodynamica Sinica, 2021 , 39 ( 6 ): 149 − 155 (in Chinese).

STEIMLE P C, KARHOFF D C, SCHRÖDER W . Unsteady transonic flow over a transport-type swept wing[J ] . AIAA Journal, 2012 , 50 ( 2 ): 399 − 415 .

DANDOIS J . Experimental study of transonic buffet phenomenon on a 3D swept wing[J ] . Physics of Fluids, 2016 , 28 ( 1 ): 016101 .

BRUNET V, DECK S. Zonal-detached eddy simulation of transonic buffet on a civil aircraft type configuration[C]// Advances in Hybrid RANS-LES Modelling. Berlin, Heidelberg: Springer, 2008: 182−191.

GROSSI F, BRAZA M, HOARAU Y . Prediction of transonic buffet by delayed detached-eddy simulation[J ] . AIAA Journal, 2014 , 52 ( 10 ): 2300 − 2312 .

SARTOR F, TIMME S . Delayed detached-eddy simulation of shock buffet on half wing-body configuration[J ] . AIAA Journal, 2017 , 55 ( 4 ): 1230 − 1240 .

GAO C Q, ZHANG W W . Numerical simulation and modal analysis of transonic buffet flow over wings[J ] . Acta Aeronautica et Astronautica Sinica, 2019 , 40 ( 7 ): 122597 (in Chinese).

IOVNOVICH M, RAVEH D E . Numerical study of shock buffet on three-dimensional wings[J ] . AIAA Journal, 2015 , 53 ( 2 ): 449 − 463 .

PALADINI E, DANDOIS J, SIPP D, et al . Analysis and comparison of transonic buffet phenomenon over several three-dimensional wings[J ] . AIAA Journal, 2019 , 57 ( 1 ): 379 − 396 .

YAMAZAKI W, YAMAGISHI S, UENO M . Investigation of indirect Reynolds number effect via computational fluid dynamics simulations[J ] . Journal of Aircraft, 2018 , 55 ( 5 ): 1805 − 1816 .

WAHLS R. The National Transonic Facility - A research retrospective[C]//39th Aerospace Sciences Meeting and Exhibit, Reno, NV, USA. Reston, Virginia: AIAA, 2001.

GREEN J, QUEST J . A short history of the European Transonic Wind Tunnel ETW[J ] . Progress in Aerospace Sciences, 2011 , 47 ( 5 ): 319 − 368 .

CURTIN M, BOGUE D, OM D, et al. Investigation of transonic Reynolds number scaling on a twin-engine transport[C]//40th AIAA Aerospace Sciences Meeting Exhibit, Reno, NV, USA. Reston, Virginia: AIAA, 2002.

LI Q, LIU D W, XU X, et al . Experimental study of aerodynamic characterictics of CHN-T1standard model in 2.4 m transonic wind tunnel[J ] . Acta Aerodynamica Sinica, 2019 , 37 ( 2 ): 337 − 344 (in Chin ese).

ZHAO Z L, WU J Q, LI H, et al . Investigation of virtual flight testing technique based on 2.4 m transonic wind tunnel[J ] . Acta Aeronautica et Astronautica Sinica, 2016 , 37 ( 2 ): 504 − 512 (in Chinese).

JONES J L. The transonic Reynolds number problem[R]. NASA, 1977.

LO C F, CARLETON W E. Transonic scaling effect on a quasi, two-dimensional C-141 airfoil model[M ] . Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1973. https://catalog.hathitrust.org/Record/102893443

WICK A T, HOOKER J R, WALKER J, et al. Hybrid wing body performance validation at the national transonic facility[C]//55th AIAA Aerospace Sciences Meeting, Grapevine, Texas. Reston, Virginia: AIAA, 2017.

PETTERSSON K, RIZZI A. Estimating Reynolds number scaling and wind tunnel boom effects with the help of CFD methods[C]//24th AIAA Applied Aerodynamics Conference, San Francisco, California. Reston, Virginia: AIAA, 2006.

WANG Y J, LIU D W, XU X, et al . Investigation of Reynolds number effects on aerodynamic characteristics of a transport aircraft[J ] . Aerospace, 2021 , 8 ( 7 ): 177 .

WU D K. Study of breaking bow wave fine flow field and hydrodynamic performance of bench mark ship models based on delayed detached eddy simulation method[D]. Shanghai: Shanghai Jiao Tong University, 2022(in Chinese).

Spalart P R, JOU W H, STRELETS, et al. Comments on the feasibility of LES for wings, and on a hybrid RANS/LES approach[C]// First AFOSR International Conference on DNS/LES, 1997.

SPALART P R, DECK S, SHUR M L, et al . A new version of detached-eddy simulation, resistant to ambiguous grid densities[J ] . Theoretical and Computational Fluid Dynamics, 2006 , 20 ( 3 ): 181 − 195 .

YANG Z C, LIU J L. A precise approach to predict transonic wing buffet boundary[J ] . Mechanical Science and Technology for Aerospace Engineering, 2013, 32(12): 1717−1721(in Chinese). https://journals.nwpu.edu.cn/jxkxyjs/article/id/5091

CHEN Z S, YU L . Buffet onset measurement technique for aircraft model in 2.4 m wind tunnel[J ] . Experiments and Measurements in Fluid Mechanics, 2004 , 18 ( 4 ): 24 − 27,33 (in Chinese).

OHMICHI Y, ISHIDA T, HASHIMOTO A. Numerical investigation of transonic buffet on a three-dimensional wing using incremental mode decomposition[C]//55th AIAA Aerospace Sciences Meeting, Grapevine, Texas. Reston, Virginia: AIAA, 2017.

浏览量

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

零质量射流控制翼型跨声速激波抖振特性

采用TRIP3.0模拟CHN-T1模型气动特性

“新一代风电空气动力学”专栏序言

高速飞行器气动推进一体化性能参数化分析

基于CFD-CSD耦合仿真的风力机气弹稳定性及载荷分析