雷诺数对增升装置流动特性影响的计算研究Ⅰ——气动力特性和汇流边界层  

Calculation Research on the Effect of Reynolds Number on the High Lift Device Flow Characteristcs Ⅰ——Aerodynamic Characteristics and Confluent Boundary Layer

作　　者：刘亦鹏[1] 高云海[1] 王继明[1] 郭传亮 焦仁山[2] 

机构地区：[1]上海飞机设计研究院,上海201210 [2]中国航空工业空气动力研究院,哈尔滨150001

出　　处：《民用飞机设计与研究》2017年第2期29-39,共11页Civil Aircraft Design & Research

基　　金：航空科学基金项目;编号:No.2015324003

摘　　要：在1×10~630×10~6的雷诺数范围内,马赫数为0.197的情况下,使用数值计算方法研究了雷诺数对NHLP-2D翼型的气动力特性和流动特性的影响。建立的数值模型考虑了汇流边界层的网格处理,与已有试验和计算结果对比分析表明本数值模型可信。计算结果表明,当雷诺数大于1.5×10~7时,雷诺数对气动力系数的影响明显减小,且小迎角下气动力随雷诺数呈线性变化趋势。汇流边界层高度随雷诺数增大而降低,缝翼和主翼产生的尾迹强度随雷诺数的增大而减弱,同时尾迹宽度逐渐减小。在高雷诺数下,襟翼尾缘处仍存在较强的缝翼尾迹,说明尾迹/边界层的相互融合作用随雷诺数增大而减小。本文为后续雷诺数对缝道流动特性的影响研究提供了基础。The aerodynamic characteristics and confluent boundary layer of NHLP-2D air foil are studied within the Reynolds number range from 1 ×10^6 to 30×10^6and Mach number 0. 197 by numerical simulation. Mesh scheme in the confluent boundary layer is carefully developed in the numerical model. Comparison with the existing test data and numerical data shows the model of present study is reliable. The Reynolds number effect on aerodynamic coefficient is obviously decreased when Re is larger than 1.5 ×10^7. And areodynamic coefficient shows a linear variation with Reynolds number for small angle of attack. As increasing Reynolds number, the thickness of confluent boudary layer decreases, and the wake intensity of slat and main element decreases. The width of wake also decreases as increasing Reynolds number. The slat wake remains strong at the trailing edge of flap at high Reynolds number which implies the interaction between wake and boundary layer decreases with the increasement of Reynolds number. The present study provides foundation for the subsequent research on the effect of Reynolds number on the slot flow.

关 键 词：增升装置 雷诺数 汇流边界层 数值模拟 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]