短舱边界层的稳定性分析及转捩预测

牛萌浩; 文豪; 韩宇峰; 苏彩虹; 孟晓轩

doi:10.7638/kqdlxxb-2021.0204

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短舱边界层的稳定性分析及转捩预测

研究论文 | 更新时间：2026-05-28

- 短舱边界层的稳定性分析及转捩预测
- Boundary-layer stability analysis and transition prediction over a nacelle
- 空气动力学学报 2022年40卷第6期页码：117-128
- 作者机构：
  
  1. 天津大学机械工程学院,天津,300072
  2. 西北工业大学航空学院,西安,710072
- 作者简介：
  
  牛萌浩（1994-），男，河南温县人，博士研究生，研究方向：流动稳定性和边界层转捩. E-mail：niumenghao@tju.edu.cn
  苏彩虹*（1979-），女，内蒙古包头人，教授，研究方向：流动稳定性和边界层转捩. E-mail：su_ch@tju.edu.cn
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0204
  中图分类号： V211.3
- 纸质出版：2022
- 稿件说明：
移动端阅览
牛萌浩, 文豪, 韩宇峰, 等. 短舱边界层的稳定性分析及转捩预测[J]. 空气动力学学报, 2022, 40(6): 117−128.

NIU Menghao, WEN Hao, HAN Yufeng, et al. Boundary-layer stability analysis and transition prediction over a nacelle[J]. 2022, 40(6): 117-128.
牛萌浩, 文豪, 韩宇峰, 等. 短舱边界层的稳定性分析及转捩预测[J]. 空气动力学学报, 2022, 40(6): 117−128. DOI： 10.7638/kqdlxxb-2021.0204

NIU Menghao, WEN Hao, HAN Yufeng, et al. Boundary-layer stability analysis and transition prediction over a nacelle[J]. 2022, 40(6): 117-128. DOI： 10.7638/kqdlxxb-2021.0204.

摘要

当边界层从层流转变为湍流时，表面摩阻显著增加。因此，准确预测短舱表面边界层的转捩位置才能准确预估表面摩阻，从而有效评估短舱外罩型面设计对全机阻力带来的影响。目前，工程上被认为最有理论根据的转捩预测方法是基于线性稳定性理论的e

方法。本文以宽体客机发动机翼吊短舱为研究对象，分析了巡航状态下短舱表面边界层的稳定性特征，并对边界层的转捩位置进行了预测。首先，基于多块网格并行计算的CFD求解器得到基本流场，采用线性稳定性理论分析了典型工况下短舱边界层的稳定性特征；之后，采用e

方法给出了短舱表面转捩线的分布，并分析了攻角和巡航马赫数变化对边界层稳定性和转捩位置的影响规律。结果表明，巡航状态下，短舱表面边界层的转捩主要由T-S波失稳导致，横流方向的速度分量大小不到边界层外缘流速的3%，横流不稳定性的影响较小。攻角增大，短舱背风面及侧面大部分区域的转捩位置前移，而迎风面附近转捩位置明显后移。马赫数越大，T-S不稳定波的频率范围和增长率均减小，边界层更稳定，转捩位置更靠后。

Abstract

As transition occurs in the boundary layer

the flow changes from a laminar state to a turbulent state

resulting in a significant increase of the skin friction. For a nacelle

an accurate prediction of its boundary layer transition is necessary for the accurate calculation of the nacelle surface friction as well as the effective evaluation of the drag on the whole airplane induced by the nacelle outline. So far

the most reliable approach of transition prediction in practice is the linear stability theory based e

method. In this work

a nacelle under the wing of a wide-body aircraft was studied

with the focus on the boundary layer stability characteristics and the transition location prediction. Firstly

the base flow was obtained by a computational fluid dynamic (CFD) solver using the multiple-block grid and parallel computation technique

and the stability characteristics of the boundary layer over the nacelle were analyzed under typical conditions using the linear stability theory. Secondly

the e

method was used to provide the transition front distributions. Effects of the angle of attack and the flight Mach number on the boundary layer stability charateristics and the transition location were quantified. The results show that the boundary layer transition over the nacelle is mainly induced by the instability of T-S waves

while the cross-flow instability is weak due to the fact that the cross-flow velocity is less than 3% of the velocity at the outer edge of the boundary layer. As the angle of attack increases

the transition location moves forward in the leeward section as well as in most of the lateral zones

while it moves backward in the windward section. With the increase of the flight Mach number

the frequency range of the T-S wave tends to shrink and its growth rate decreases

the boundary layer becomes more stable

and the transition location appears further downstream.

关键词

Keywords

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