柔性仿羽毛结构抑制边界层转捩的初步探索

叶正寅; 洪正; 武洁

doi:10.7638/kqdlxxb-2020.0094

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 >

柔性仿羽毛结构抑制边界层转捩的初步探索

专栏——国家数值风洞自主可控关键技术 | 更新时间：2026-05-28

- 柔性仿羽毛结构抑制边界层转捩的初步探索
- Suppression of flexible feather-like structure on boundary layer transition
- 空气动力学学报 2020年38卷第6期页码：1173-1182
- 作者机构：
  
  西北工业大学,西安,710072
- 作者简介：
  
  叶正寅(1963-), 男, 教授, 研究方向:空气动力学.E-mail:yezy@nwpu.edu.cn
- 基金信息：
  
  国家数值风洞工程;“翼型叶栅空气动力学”重点实验室稳定支持项目（JCKYS2019607008）
- DOI：10.7638/kqdlxxb-2020.0094
  中图分类号： V211.3;O357.4
- 纸质出版：2020
- 稿件说明：
移动端阅览
叶正寅, 洪正, 武洁. 柔性仿羽毛结构抑制边界层转捩的初步探索[J]. 空气动力学学报, 2020, 38(6): 1173-1182.

YE Zhengyin, HONG Zheng, WU Jie. Suppression of flexible feather-like structure on boundary layer transition[J]. 2020, 38(6): 1173-1182.
叶正寅, 洪正, 武洁. 柔性仿羽毛结构抑制边界层转捩的初步探索[J]. 空气动力学学报, 2020, 38(6): 1173-1182. DOI： 10.7638/kqdlxxb-2020.0094.

YE Zhengyin, HONG Zheng, WU Jie. Suppression of flexible feather-like structure on boundary layer transition[J]. 2020, 38(6): 1173-1182. DOI： 10.7638/kqdlxxb-2020.0094.

摘要

通过观察，发现存在展向流动时鸟类柔性的羽毛侧缘会卷起，这对展向流动起到了额外的阻碍作用，即流向和展向的阻力特征是不同的。为了研究羽毛表面的这种各向异性阻力特征对边界层转捩流动的影响，本文从宏观角度出发建立了一种唯象力学模型来刻画表面的各向异性。然后，运用直接数值模拟的方法研究了该模型对平板边界层转捩的影响。自由来流马赫数为0.2，基于入口处边界层排移厚度的雷诺数为732。研究结果表明，在模型抑制展向流动的作用下，平板边界层转捩明显推迟，不同的参数下至少可以推迟一倍以上距离。即使在流动进入湍流状态后，壁面的摩擦阻力系数也大大降低，维持在与层流摩擦系数相当的水平。转捩位置的推迟和湍流区摩擦阻力的降低都有利于降低平板的阻力。如果考虑卷起的羽毛侧缘对流向流动带来额外阻力，这会使得转捩提前，减阻的效果降低。此研究结果一方面揭示了鸟类飞行的部分奥秘，另一方面也为边界层被动控制措施提供了一种新的思路。

Abstract

It is observed that when there is spanwise flow

the soft side edges of bird feathers are blown up

and thus the spanwise flow is resisted

i.e.

the drag characteristics for streamwise direction and spanwise direction on the feather surface are quite different. In order to study the influence of this anisotropic characteristics of feathers on the laminar-turbulent transition in boundary layer flow

a phenomenological mechanical model

from the macroscopic view

is established to describe the anisotropic characteristics of bird feathers. By means of direct numerical simulation with finite difference method

the model is imposed to the transitional flow over a flat plate

where the freestream Mach number is 0.2 and the Reynolds number based on the displacement thickness of boundary layer at the inlet is 732. Numerical results show that when the spanwise flow is damped by the anisotropic model

the laminar-turbulent transition is significantly delayed

and even the friction in turbulent region is reduced to be almost the same level as that in laminar region. The stronger the damping for spanwise flow by the model

the more obvious the transition delay and friction reduction. Both the delay of transition and the reduction of friction drag in turbulent region are helpful to reduce the overall drag of the flat plate. When considering the influence of blown-up feathers on streamwise direction in the form of resistance

the resistance in streamwise direction results in the earlier onset of transition. Although friction drag is further reduced in this case

while the total drag of flat plate is increased. Overall

this study reveals some of the mysteries of bird flight

and also provides a new idea for the passive control of the boundary layer flow.

关键词

Keywords

references

ROLSTON S. High Reynolds number tools and techniques for civil aircraft design-An overview of the European 'HiReTT' project[C ] //Proc of the 19th AIAA Applied Aerodynamics Conference, Anaheim, CA, USA. Reston, Virigina: AIAA. DOI: 10.2514/6.2001-2411

Van DAM C P. The aerodynamic design of multi-element high-lift systems for transport airplanes[J]. Progress in Aerospace Sciences, 2002, 38(2):101-144. DOI:10.1016/S0376-0421(02)00002-7

SCHRAUF G. Status and perspectives of laminar flow[J]. The Aeronautical Journal, 2005, 109(1102):639-644. DOI:10.1017/s000192400000097x

ZHAOG F. Role of suction and pressuregradientin the transition procces of boundary layer[J]. Acta Mechanica Sinica, 1994, 26(5):631-635.(in Chinese)

CHOI K S. Near-wall structure of a turbulent boundary layer with riblets[J]. Journal of Fluid Mechanics, 1989, 208:417-458. DOI:10.1017/s0022112089002892

BECHERT D W, BARTENWERFER M. The viscous flow on surfaces with longitudinal ribs[J]. Journal of Fluid Mechanics, 1989, 206:105-129. DOI:10.1017/s0022112089002247

WANG J J. Reviews and prospects in turbulent drag reduction over riblets surface[J]. Journal of Beijing University of Aeronautics and Astronautics, 1998, 24(1):3-5.(in Chinese) DOI:10.3969/j.issn.1001-5965.1998.01.009

TARDU S F. Active control of near-wall turbulence by local oscillating blowing[J]. Journal of Fluid Mechanics, 2001, 439:217-253. DOI:10.1017/s0022112001004542

GUO H, LI X B, WANG H W, et al. Experimental study on boundary-layer transition control byspanwise discrete suction[J]. Journal of Experiments in Fluid Mechanics, 2014, 28(6):13-19.(in Chinese)

PANG J G, CHOI K S. Turbulent drag reduction by Lorentz force oscillation[J]. Physics of Fluids, 2004, 16(5):L35-L38. DOI:10.1063/1.1689711

DU Y Q, KARNIADAKIS G E. Suppressing wall turbulence by means of a transverse traveling wave[J]. Science, 2000, 288(5469):1230-1234. DOI:10.1126/science.288.5469.1230

SINHA S, ZOU J. On controlling flows with micro-vibratory wall motion[C ] //Proc of the 18th Applied Aerodynamics Conference, Denver, CO, USA. Reston, Virigina: AIAA. DOI: 10.2514/6.2000-4413

BAI H L, ZHOU Y, ZHANG W G, et al. Active control of a turbulent boundary layer based on local surface perturbation[J]. Journal of Fluid Mechanics, 2014, 750:316-354. DOI:10.1017/jfm.2014.261

CARPENTER P W, MORRIS P J. The effect of anisotropic wall compliance on boundary-layer stability and transition[J]. Journal of Fluid Mechanics, 1990, 218:171. DOI:10.1017/s0022112090000970

ZHANG Q L, LI J B. Control of boundary layer transition using active compliant wall motion[J].Acta Aerodynamica Sinica, 1999, 17(3):333-338.(in Chinese) DOI:10.3969/j.issn.0258-1825.1999.03.015

BAI H L, KEVIN, HUTCHINS N, et al. Turbulence modifications in a turbulent boundary layer over a rough wall with spanwise-alternating roughness strips[J]. Physics of Fluids, 2018, 30(5):055105. DOI:10.1063/1.5026134

LIU H P, GAO Z X, JIANG C W, et al. Review of researches on compressible turbulent boundary layer combustion for skin friction reduction[J]. Acta Aerodynamica Sinica, 2020, 38(3):293-602.(in Chinese)

DENG L, QIAO Z D, XIONG J T, et al. Multi-objective inverse design of natural laminar flow airfoils[J].Acta Aeronautica et Astronautica Sinica, 2010, 31(7):1373-1378.(in Chinese)

GUO Q L, TU G H, CHEN J Q, et al. Control of hypersonic boundary layer instability by transverse rectangular micro-cavities[J]. Journal of Aerospace Power, 2020, 35(1):135-143.(in Chinese) DOI:10.13224/j.cnki.jasp.2020.01.016

ZHOU Y L, LIU W, WU D. Application of different roughness shapes in inducing supersonic boundary layer transition[J]. Journal of National University of Defense Technology, 2018, 40(6):17-22.(in Chinese) DOI:10.11887/j.cn.201806003

QU Q L, WANG J J. Human flight inspired by the aerodynamics of bird flight[J]. Physics, 2016, 45(10):640-644.(in Chinese) DOI:10.7693/wl20161003

TUCKER A V, PARROTT C G. Aerodynamics of gliding flight in a falcon and other birds[J]. Journal of Experimental Biology, 1970, 52(2):345-367.

PARFITT A R, VINCENT J F V. Drag reduction in a swimming Humboldt penguin, Spheniscus humboldti, when the boundary layer is turbulent[J]. Journal of Bionic Engineering, 2005, 2(2):57-62. DOI:10.1007/bf03399481

LI C B. On the formation of thestreamwise vortex in a transitional boundary layer[J]. Acta Physica Sinica, 2001, 50(1):182-184.(in Chinese) DOI:10.3321/j.issn:1000-3290.2001.01.035

CHEN L. Studies of vortical structures and transition mechanisms in transitional boundary layers[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2010.(in Chinese)

唐洪涛.不可压缩平板边界层从层流突变为湍流的机理及湍流特性[D].天津: 天津大学, 2007.

WANG Y Q. Research on turbulence generation and sustenance based on DNS of transitional boundary layer[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2016.(in Chinese)

HUANG Z F. The mechanism of laminar-turbulent transition and the characteristics of turbulence in a supersonic boundary layer on a flat plate[D]. Tianjin: Tianjin University, 2006.(in Chinese)

YANG Q, YUAN X X, CHEN J Q, et al. On elementary coherent structures in incompressible wall-bounded turbulence[J]. Acta Aerodynamica Sinica, 2020, 38(1):83-99.(in Chinese)

LIAO F, YE Z Y, ZHANG L X. Extending geometric conservation law to cell-centered finite difference methods on stationary grids[J]. Journal of Computational Physics, 2015, 284:419-433. DOI:10.1016/j.jcp.2014.12.040

LI N, LUO J S. Transition mechanism of an incompressible boundary layer on a flat plate[J]. Journal of Aerospace Power, 2013, 28(4):743-751.(in Chinese) DOI:10.13224/j.cnki.jasp.2013.04.001

SAYADI T, MOIN P. A comparative study of subgrid scale models for the prediction of transition in turbulent boundary layers[J]. Center for Turbulence Research Annual Research Briefs, 2010:237-247.

COMTE F D P, LESIEUR M. Large-eddy simulation of transition to turbulence in a boundary layer developing spatially over a flat plate[J]. Journal of Fluid Mechanics, 1996, 326:1-36. DOI:10.1017/s0022112096008221

XU C X. Coherent structures and drag-reduction mechanism in wall turbulence[J]. Advances in Mechanics, 2015, 45(1):111-140.(in Chinese) DOI:10.6052/1000-0992-15-006

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

基于OpenCFD-Comb的高焓湍流边界层气体注入的直接数值模拟

高超声速边界层转捩的若干问题及工程应用研究进展综述

边界层转捩预测中的局部散射理论

关键参数对高速圆锥边界层来流慢声波扰动感受性的影响规律

带水平剪切的温盐稳定分层流动数值模拟