The effect of alula's sweep angle on wing lift augmentation

TANG Yuhan; WANG Jiangsheng; WANG Jinjun

doi:10.7638/kqdlxxb-2023.0178

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

The effect of alula's sweep angle on wing lift augmentation

更新时间：2026-05-28

- The effect of alula's sweep angle on wing lift augmentation
- Vol. 42, Issue 2, Pages: 76-84(2024)
- 作者机构：
  
  北京航空航天大学流体力学教育部重点实验室,北京,100191
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2023.0178
  CLC： O355
- Published：2024
- 稿件说明：
移动端阅览
唐钰涵, 王将升, 王晋军. 小翼羽掠角对机翼增升效果的影响[J]. 空气动力学学报, 2024, 42(2): 76−84.

TANG Yuhan, WANG Jiangsheng, WANG Jinjun. The effect of alula's sweep angle on wing lift augmentation[J]. 2024, 42(2): 76-84.
唐钰涵, 王将升, 王晋军. 小翼羽掠角对机翼增升效果的影响[J]. 空气动力学学报, 2024, 42(2): 76−84. DOI： 10.7638/kqdlxxb-2023.0178

TANG Yuhan, WANG Jiangsheng, WANG Jinjun. The effect of alula's sweep angle on wing lift augmentation[J]. 2024, 42(2): 76-84. DOI： 10.7638/kqdlxxb-2023.0178.

摘要

鸟类会通过抬起其翅膀前缘3至4根长度较短的羽毛（小翼羽）来抑制失速和增加升力，并根据不同飞行状态改变小翼羽与翅膀之间的掠角。为应对大迎角下的机翼失速问题，本文结合风洞测力和粒子图像测速实验研究了小翼羽掠角对机翼增升效果的影响。风洞测力实验结果表明，相比于无前掠的小翼羽，适当前掠的小翼羽对机翼的增升效果更好且不会增加机翼阻力。平面粒子图像测速和体视粒子图像测速实验表明，适当的前掠角能够增强小翼羽产生的前缘涡的强度，并扩大前缘涡增升的有效机翼迎角范围，最终导致适当前掠的小翼羽对机翼的增升效果更好。

Abstract

Birds deploy several short feathers called alula at the leading edge of wings to suppress stall and increase lift. The sweep angle between the alula and the wing is adjusted according to different flight states. The effects of the alula sweep angle on the aerodynamic performance of the rectangular wing are therefore investigated by utilizing force measurement and particle image velocimetry. Compared to an alula with a zero sweep angle

an alula with an appropriate non-zero forward sweep angle can increase the lift and does not introduce extra drag

thus improves considerably the aerodynamic performance. The underline mechanism is revealed by the flow fields measured by planar and stereo particle image velocimetries

which demonstrate that the alula with an appropriate non-zero forward sweep angle enhances the strength of the leading edge vortex over the wing and broadens the range of angle of attack in which the leading edge vortex can increase the lift.

关键词

Keywords

references

CARRUTHERS A, TAYLOR G, WALKER S, et al. Use and function of a leading edge flap on the wings of eagles[C]// 45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virigina: AIAA, 2007. doi: 10.2514/6.2007-43

CARRUTHERS A C, THOMAS A L R, TAYLOR G K. Automatic aeroelastic devices in the wings of a steppe eagle Aquila nipalensis[J]. The Journal of Experimental Biology, 2007, 210(Pt 23): 4136-4149. doi: 10.1242/jeb.011197

MCMASTERS J H. Reflections of a paleoaerodynamicist[J]. MycoKeys, 1986, 29(3 pt 1): 331-384. doi: 10.1353/pbm.1986.0061

AZUMA A. Flight by gliding[M]//The Biokinetics of Flying and Swimming. 2nd Edition. Reston, VA: AIAA, 2006: 33-122. doi: 10.2514/5.9781600862502.0033.0122

ITO M R, DUAN C F, WISSA A A. The function of the alula on engineered wings: A detailed experimental investigation of a bioinspired leading-edge device[J]. Bioinspiration Biomimetics, 2019, 14(5): 056015. doi: 10.1088/1748-3190/ab36ad

LINEHAN T, MOHSENI K. Investigation of a sliding alula for control augmentation of lifting surfaces at high angles of attack[J]. Aerospace Science and Technology, 2019, 87: 73−88. doi: 10.1016/j.ast.2019.02.008

MANDADZHIEV B A. Design and aerodynamic analysis of an airfoil with a bioinspired leading edge device for stall mitigation at low Reynolds number operation[D]. Urbana Champaign, Illinois, USA: University of Illinois at Urbana-Champaign, 2017.

MANDADZHIEV B A, LYNCH M K, CHAMORRO L P, et al. An experimental study of an airfoil with a bio-inspired leading edge device at high angles of attack[J]. Smart Materials and Structures, 2017, 26(9): 094008. doi: 10.1088/1361-665x/aa7dcd

LINEHAN T, MOHSENI K. On the maintenance of an attached leading-edge vortex via model bird alula[J]. Journal of Fluid Mechanics, 2020, 897: A17. doi: 10.1017/jfm.2020.364

SANDER A. The role of the alula in avian flight and its application to small aircraft: a numerical study[D]. Groningen, Netherlands: University of Groningen, 2018.

LINEHAN T, MOHSENI K. Scaling trends of bird’s alular feathers in connection to leading-edge vortex flow over hand-wing[J]. Scientific Reports, 2020, 10: 7905. doi: 10.1038/s41598-020-63181-7

LINEHAN T I, MOHSENI K, FERRAR J. Active roll control at high angles of attack via bio-inspired sliding alula[C]// AIAA Scitech 2020 Forum, Orlando, FL. Reston, Virginia: AIAA, 2020. doi: 10.2514/6.2020-1541

JARDIN T, DAVID L. Spanwise gradients in flow speed help stabilize leading-edge vortices on revolving wings[J]. Physical Review E, Statistical, Nonlinear, and Soft Matter Physics, 2014, 90(1): 013011. doi: 10.1103/PhysRevE.90.013011

WONG J, RIVAL D. Determining the relative stability of leading-edge vortices on nominally two-dimensional flapping profiles[J]. Journal of Fluid Mechanics, 2015, 766: 611−625. doi: 10.1017/jfm.2015.39

ELDREDGE J D, JONES A R. Leading-edge vortices: Mechanics and modeling[J]. Annual Review of Fluid Mechanics, 2019, 51(1): 75−104. doi: 10.1146/annurev-fluid-010518-040334

ADHIKARI D R, LOUBIMOV G, KINZEL M P, et al. Effect of wing sweep on a perching maneuver[J]. Physical Review Fluids, 2022, 7(4): 044702. doi: 10.1103/PhysRevFluids.7.044702

CHAMPAGNAT F, PLYER A, LE BESNERAIS G, et al. Fast and accurate PIV computation using highly parallel iterative correlation maximization[J]. Experiments in Fluids, 2011, 50(4): 1169−1182. doi: 10.1007/s00348-011-1054-x

PAN C, XUE D, XU Y, et al. Evaluating the accuracy performance of Lucas-Kanade algorithm in the circumstance of PIV application[J]. Science China Physics, Mechanics Astronomy, 2015, 58(10): 104704. doi: 10.1007/s11433-015-5719-y

SOLOFF S M, ADRIAN R J, LIU Z C. Distortion compensation for generalized stereoscopic particle image velocimetry[J]. Measurement Science and Technology, 1997, 8(12): 1441−1454. doi: 10.1088/0957-0233/8/12/008

ZHOU Y, ALAM M M, YANG H X, et al. Fluid forces on a very low Reynolds number airfoil and their prediction[J]. International Journal of Heat and Fluid Flow, 2011, 32(1): 329−339. doi: 10.1016/j.ijheatfluidflow.2010.07.008

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Numerical simulation of hypersonic magnetofluid control based on non-linear coupling constitutive relation

Calibration modeling of wind tunnel balance based on multivariate orthogonal functions

Influence of slotted track on aerodynamic characteristics of high-speed maglev train

Research status of aerodynamic design for integrated propulsion and airframe in near-space high-altitude long-endurance (HALE) UAVs

Preface to the special column on “UAV Aero-Propulsive Integration Design”

Related Author

Shi Hao

Xiao Hong

Zhou Li

Wang Zhanxue

Yan Wanfang

Wei Wei

Jiang Kun

Wei Zhongwu

Related Institution

Collaborative Innovation Center for Advanced Aero-Engine, Beijing

School of Power and Energy, Northwestern Polytechnical University, Xi'an

China Academy of Aerospace Aerodynamics, Beijing

Key Laboratory of Traffic Safety on the Track of Ministry of Education, Central South University, Changsha

China Railway Siyuan Survey and Design Group Co., Ltd, Wuhan

AI问答

⁰