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

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。

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-Reynoldsnumber 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.