定常黏性外流气动力分量的同源性及流场断层扫描诊断原理

邹舒帆; 吴介之

doi:10.7638/kqdlxxb-2019.0099

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定常黏性外流气动力分量的同源性及流场断层扫描诊断原理

研究论文 | 更新时间：2026-05-28

- 定常黏性外流气动力分量的同源性及流场断层扫描诊断原理
- Homology of aerodynamic force components and principle of aerodynamic computed topography in steady viscous external flow
- 空气动力学学报 2019年37卷第6期页码：871-882
- 作者机构：
  
  北京大学工学院湍流与复杂系统国家重点实验室,北京,100871
- 作者简介：
  
  邹舒帆(1991-), 男, 湖南新化人, 博士, 研究方向:空气动力学, 涡动力学.E-mail:zousf@pku.edu.cn
  吴介之(1940-), 男, 广东肇庆人, 教授, 研究方向:空气动力学, 涡动力学.E-mail:jzwu@coe.pku.edu.cn
- 基金信息：
  
  国家自然科学基金（11472016）
- DOI：10.7638/kqdlxxb-2019.0099
  中图分类号： V211.3
- 纸质出版：2019
- 稿件说明：
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邹舒帆, 吴介之. 定常黏性外流气动力分量的同源性及流场断层扫描诊断原理[J]. 空气动力学学报, 2019, 37(6): 871-882.

ZOU Shufan, WU Jiezhi. Homology of aerodynamic force components and principle of aerodynamic computed topography in steady viscous external flow[J]. 2019, 37(6): 871-882.
邹舒帆, 吴介之. 定常黏性外流气动力分量的同源性及流场断层扫描诊断原理[J]. 空气动力学学报, 2019, 37(6): 871-882. DOI： 10.7638/kqdlxxb-2019.0099.

ZOU Shufan, WU Jiezhi. Homology of aerodynamic force components and principle of aerodynamic computed topography in steady viscous external flow[J]. 2019, 37(6): 871-882. DOI： 10.7638/kqdlxxb-2019.0099.

摘要

减阻是空气动力学的基本任务之一。传统流场诊断和减阻方案基于线性分解、各个击破和线性叠加的思路。最近的研究表明：对于给定构型与流动条件的定常绕流，型阻和诱导阻力不是纯数而是尾流截面位置的函数，而且目前广泛采用的诱导阻力公式仅适用于简单附着流。基于这些认识，证明了升力、型阻和诱导阻力在物理上是同源的，可分别定义为Lamb矢量的体积分或其矩的面积分；面对真实的复杂流场，提出了采用Lamb矢量场在一族流场截面上的性状来定义和诊断升力、阻力各分量的技术原理，作为对传统方法的扬弃。以大攻角三角翼流场为例，采用该原理判明了气动力分量对应的流动结构，指出三角翼尾部的二次涡产生负升力和型阻峰值。该结构可以根据边界涡量动力学溯源到局部壁面区域，从而提出了增加升阻比的概念性优化方案。

Abstract

Drag reduction is one of the major tasks of aerodynamics. Traditional principles of flow diagnosis and drag reduction are based on concepts of linear-decomposition/superposition. In our recent work

for steady flows around a given configuration and flow condition

the induced drag as well as the profile drag has been found to depend on the streamwise location of the wake planes

and the widely-used existing theories can only be applied to simple attached flow. Based on these findings

all force components and their correlation are proved to have a common root at the Lamb-vector field produced by the body's steady motion. In order to diagnose complex flows

a new technical principle is proposed in this article

which defines aerodynamic components by using Lamb-vector field observed on a chosen set of planes in the flow field. As an example

the steady separated flow over a slender delta wing at large angles of attack is computed to determine the flow structures responsible for the aerodynamic force components. It is pointed out that the secondary vortex structure near the wingtip produces negative lift and profile drag. The root of the structure can be traced back to the specific area of the wall according to the boundary vorticity dynamics

which then guides a conceptual configuration optimization to increase the lift-to-drag ratio.

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Keywords

references

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