先进飞行器雷诺数效应若干研究进展及展望

吴继飞; 孔文杰; 李国帅; 田书玲

doi:10.7638/kqdlxxb-2024.0063

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先进飞行器雷诺数效应若干研究进展及展望

高雷诺数复杂流动问题研究 | 更新时间：2026-07-27

- 先进飞行器雷诺数效应若干研究进展及展望
- Progress and prospect on Reynolds number effects of advanced aircraft
- 空气动力学学报 2024年42卷第8期页码：35-59
- 作者机构：
  
  1. 中国空气动力研究与发展中心高速空气动力研究所,绵阳,62100
  2. 南京航空航天大学航空学院,南京,210016
- 作者简介：
  
  吴继飞（1980—），男，安徽亳州人，博士，研究方向：试验空气动力学. E-mail：kkwjf@126.com
  孔文杰*（1994—），男，河南信阳人，博士研究生，研究方向：前沿流动控制. E-mail： kwenjie@nuaa.edu.cn
  李国帅*（1987—），男，河南濮阳人，博士，研究方向：低温试验技术研发与应用. E-mail：liguoshuai@cardc.cn
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0063
  中图分类号： V211.74
- 纸质出版：2024
- 稿件说明：
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吴继飞, 孔文杰, 李国帅, 等. 先进飞行器雷诺数效应若干研究进展及展望[J]. 空气动力学学报, 2024, 42(8): 35−59.

WU Jifei, KONG Wenjie, LI Guoshuai, et al. Progress and prospect on Reynolds number effects of advanced aircraft[J]. 2024, 42(8): 35-59.
吴继飞, 孔文杰, 李国帅, 等. 先进飞行器雷诺数效应若干研究进展及展望[J]. 空气动力学学报, 2024, 42(8): 35−59. DOI： 10.7638/kqdlxxb-2024.0063

WU Jifei, KONG Wenjie, LI Guoshuai, et al. Progress and prospect on Reynolds number effects of advanced aircraft[J]. 2024, 42(8): 35-59. DOI： 10.7638/kqdlxxb-2024.0063.

摘要

雷诺数效应对先进飞行器气动特性预测至关重要，其影响着飞行器飞行性能、研制成本和安全。本文深入探讨了3个核心问题：首先，介绍了不同研究手段在探索雷诺数效应上的优势和局限，特别强调大型低温风洞是获取真实飞行雷诺数气动特性数据的有效途径；其次，详细分析了大飞机等先进飞行器在高雷诺数下呈现的复杂流动现象及其对气动特性的影响，如多段翼型的缝道流动、超临界翼型的激波/边界层干扰、飞行器的过失速机动特性以及飞翼布局飞行器的进气道性能等，并揭示了高雷诺数效应的非线性和复杂性；最后，探讨了修正雷诺数效应的方法，强调了融合风洞试验、数值计算和飞行试验数据的重要性，通过分析现有修正模型的适用范围和局限性，提出了发展更完善的修正模型和算法的建议。文章还对雷诺数效应的未来研究方向进行了研判和展望。

Abstract

The Reynolds number effect is one of the key factors for predicting the aerodynamic characteristics of advanced aircraft since it affects flight performance and development costs. This paper provides a comprehensive discussion of three major aspects of the Reynolds number effects of aircraft. Firstly

the advantages and limitations of different research methods in exploring the Reynolds number effect are introduced

with particular emphasis on large low-temperature wind tunnels as an effective way to obtain the aerodynamic characteristics of real flight Reynolds numbers. Secondly

the nonlinearity and complexity of high-Reynolds-number flow fields and their effects on aerodynamic characteristics are thoroughly analyzed. This analysis encompass diverse scenarios including slot flows around multi-element airfoils

shock-wave/boundary layer interaction over supercritical airfoils

high-angle-of-attack fighters

and inlet performance of flying wing configurations. Finally

correction methods for the Reynolds number effects are discussed

underscoring the importance of integrating wind tunnel experiments

numerical simulations

and flight tests. Based on a rigorous analysis of existing correction models' performance

insights are provided for developing more precise correction frameworks. In summary

the overview presented in this paper serves as a valuable reference for deepening our understanding of high Reynolds number effects

advancing the development of efficient simulation methods

enhancing aircraft design levels

and provides technical guidance for advanced aircraft development.

关键词

Keywords

references

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