后缘发散翼型在宽体客机机翼设计中的应用

薛帮猛; 任启龙; 林大楷

doi:10.7638/kqdlxxb-2021.0207

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 >

后缘发散翼型在宽体客机机翼设计中的应用

翼型研究新进展 | 更新时间：2026-05-28

- 后缘发散翼型在宽体客机机翼设计中的应用
- Applications of divergent trailing edge airfoil in wide-body airliner wing design
- 空气动力学学报 2021年39卷第6期页码：128-135
- 作者机构：
  
  中国商飞北京民用飞机技术研究中心民用飞机设计数字仿真北京市重点实验室,北京,102211
- 作者简介：
  
  薛帮猛*（1978-），男，辽宁西丰人，研究员，研究方向：民用飞机气动设计. E-mail：xuebangmeng@comac.cc
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0207
  中图分类号： V211.41
- 纸质出版：2021
- 稿件说明：
移动端阅览
薛帮猛, 任启龙, 林大楷. 后缘发散翼型在宽体客机机翼设计中的应用[J]. 空气动力学学报, 2021, 39(6): 128−135.

XUE Bangmeng, REN Qilong, LIN Dakai. Applications of divergent trailing edge airfoil in wide-body airliner wing design[J]. 2021, 39(6): 128-135.
薛帮猛, 任启龙, 林大楷. 后缘发散翼型在宽体客机机翼设计中的应用[J]. 空气动力学学报, 2021, 39(6): 128−135. DOI： 10.7638/kqdlxxb-2021.0207

XUE Bangmeng, REN Qilong, LIN Dakai. Applications of divergent trailing edge airfoil in wide-body airliner wing design[J]. 2021, 39(6): 128-135. DOI： 10.7638/kqdlxxb-2021.0207.

摘要

用计算流体力学手段，研究了在宽体客机机翼剖面上施加后缘发散修形设计可获得的收益。提出了一种使用幂函数表达扰动量的后缘发散修形设计方法，使用该方法研究了扰动幂次和后缘厚度对超临界翼型气动性能的影响规律，并对比了雷诺数4×10

和2×10

下后缘厚度对翼型阻力、力矩影响的差异。研究结果表明，后缘厚度是后缘发散翼型的关键参数，相同后缘厚度下雷诺数2×10

的减阻效果不及雷诺数4×10

。雷诺数2×10

下，考虑跨声速减阻、亚声速增阻和低头力矩等因素后，后缘厚度取3‰

左右较为有利。尝试了后缘发散设计的两种应用思路，一是用来换取翼型厚度增加，二是用来调整机翼载荷分布。在翼型设计应用中，发现后缘厚度增加2‰

的修形量可使得最大相对厚度10.2%的超临界翼型在厚度放大到11.5%后仍具有不低于初始的升阻性能。在某宽体客机机翼方案上应用内翼1‰

和外翼2‰

的后缘厚度增量后，机翼-机身-短舱-吊挂构型可获得超过2 counts（1 count = 阻力系数0.0001）的阻力下降，而不付出机翼厚度和阻力发散性能代价。

Abstract

Computational fluid dynamics (CFD) method is used to evaluate the benefits of divergent trailing edge (DTE) modification in the wing design of a wide-body airliner. A power function is proposed to describe the disturbance for DTE

and effects of the power number and the trailing-edge thickness on the aerodynamic performance of a supercritical airfoil are studied

with comparison of the difference in the lift force and momentum between two Reynolds numbers

i.e.

4×10

and 2×10

. It shows that the trailing-edge thickness is a key parameter of the DTE airfoil. For the same trailing-edge thickness

the drag reduction at

= 2×10

is less than that at

= 4×10

. By taking into account the transonic drag reduction

subsonic drag and nose-down pitching moment increment at

= 2×10

it is more reasonable to take the trailing-edge thickness around 3‰

. Two applications of the DTE design have been explored

i.e. exchanging for airfoil thickness increment

and adjusting the wing load distribution. With the DTE modification of a supercritical airfoil

a 2‰

increment of the trailing-edge thickness leads to the maximum relative thickness of the airfoil increased from 10.2% to 11.5%

while the lift-drag performance is still kept at the same level of the original one. When a trailing-edge thickness increment of 1‰

at inboard and 2‰

at outboard is applied to the wing of a wide-body airliner

a drag reduction of more than 2 counts (1 count = drag coefficient 0.0001) can be achieved in the wing-fuselage-nacelle-pylon configuration

without any penalty of wing thickness and drag divergence performance loss.

关键词

Keywords

references

HARRIS C D. Wind-tunnel investigation of effects of trailing-edge geometry on a NASA supercritical airfoil section[R ] . NASA TM-X-2336, 1971. https://ntrs.nasa.gov/api/citations/19780019136/downloads/19780019136.pdf

GREGG R D, HOCH R W, HENNE P A. Application of divergent trailing edge airfoil technology to the design of a derivative wing[R ] // SAE Transactions 98 (1989): 1587-1599. SAE TP 892288, 1989. doi: 10.4271/892288

HENNE P, GREGG R. A new airfoil design concept[C ] //7th Applied Aerodynamics Conference, Seattle, WA, USA. Reston, Virigina: AIAA, 1989. AIAA 89-2201. doi: 10.2514/6.1989-2201

EL-GAMMAL M, NAUGHTON J W, HANGAN H. Drag force balance of a blunt and divergent trailing-edge airfoil[J]. Journal of Aircraft, 2010, 47(1): 345-348. DOI:10.2514/1.46308

KOSS D, BAUMINGER S, SHEPSHELOVICH M, et al. Pilot test of a lo w Reynolds number DTE-airfoil[C ] //31st Aerospace Sciences Meeting, Reno, NV. Reston, Virginia: AIAA, 1993. AIAA 93-0643. doi: 10.2514/6.1993-643

THOMPSON B E, LOTZ R D. Divergent-trailing-edge airfoil flow[J]. Journal of Aircraft, 1996, 33(5): 950-955. DOI: 10.2514/3.47040DOI:10.1017/s0022112098002699

THOMPSON B, LOTZ R. Flow around a blunt and divergent trailing edge[J]. Experiments in Fluids, 2002, 33(3): 374-383. DOI:10.1007/s00348-002-0421-z

EL-GAMMAL M, HANGAN H. Three-dimensional wake dynamics of a blunt and divergent trailing edge airfoil[J]. Experiments in Fluids, 2008, 44(5): 705-717. DOI:10.1007/s00348-007-0428-6

HUNTER A, THOMPSON B E. Turbulent separated flow over a rounded divergent trailing edge[C]//45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virginia: AIAA, 2007. AIAA 2007-274. doi:10.2514/6.2007-274

SEFCOVIC J A, SMITH D R. Aerodynamic control of a semi-span wing with a divergent trailing edge using synthetic jets[C ] //27th AIAA Applied Aerodynamics Conference, San Antonio, Texas. Reston, Virginia: AIAA, 2009. AIAA 2009-3621. doi: 10.2514/6.2009-3621

SEFCOVIC J A, SMITH D R. Proportional aerodynamic control of a swept divergent trailing edge wing using synthetic jets[C ] //48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Orlando, Florida. Reston, Virginia: AIAA, 2010. AIAA 2010-92. doi: 10.2514/6.2010-92

HENNE P A. Innovation with computational aerodynamics: the divergent trailing-edge airfoil[M ] //Applied Computational Aerodynamics. Washington DC: AIAA, 1990: 221-261. doi: 10.2514/5.9781600865985.0221.0261

YOO N S. Aerodynamic performance improvement by divergent trailing edge modification to a supercritical airfoil[J]. KSME International Journal, 2001, 15(10): 1434-1441. DOI:10.1007/BF03185685

THOMPSON B E, LOTZ R D. Reynolds number effects on divergent trailing edge airfoils in transonic flow[C]//ASME Fluids Engineering Division Summer Meeting, 1997.

CARUANA D, MIGNOSI A, ROBITAILLIÉ C, et al. Separated flow and buffeting control[J]. Flow, Turbulence and Combustion, 2003, 71(1-4): 221-245. DOI:10.1023/B: APPL.0000014918.93432.4f

CARUANA D, MIGNOSI A, CORRÈGE M, et al. Buffet and buffeting control in transonic flow[J]. Aerospace Science and Technology, 2005, 9(7): 605-616. DOI:10.1016/j.ast.2004.12.005

LI Y C, WANG J J, HUA J. Experimental investigations on the effects of divergent trailing edge and Gurney flaps on a supercritical airfoil[J]. Aerospace Science and Technology, 2007, 11(2-3): 91-99. DOI:10.1016/j.ast.2006.01.006

陆超. 翼型改型对超临界翼型气动性能影响的研究[D]. 沈阳: 沈阳航空工业学院, 2009.

XUE B M, ZHANG W S, ZHANG Z X. Multi-objective wing optimization of civil aircrafts in engine-aircraft integration configuration[J]. Acta Aerodynamica Sinica, 2018, 36(6): 941-948. (in Chinese)

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

考虑稀薄效应的再入飞行器前缘热化学反应与烧蚀模型研究

个体间距对多扑翼气动噪声的影响特性

基于条件扩散模型的火箭气动外形快速设计方法

基于AENS仿真平台的螺旋度修正湍流模型研究

氢气驱动激波风洞高焓流场建立过程的数值模拟研究