雷诺数对增升装置流动特性影响的计算研究Ⅱ——缝道流动特性  

Calculation Research on the Effect of Reynolds Number on the High Lift Device Flow Characteristcs Ⅱ——Slot Flow Characteristics

作　　者：刘亦鹏[1] 陈莹[1] 高云海[1] 郭传亮 焦仁山[2] LIU Yipeng;CHEN Ying;GAO Yunhai;GUO Chuanliang;JIAO Renshan(Shanghai Aircraft Design and Research Institute, Shanghai 201210, China;Chinese Aerodynamics Research Institute of Aeronautics, Harbin 150001, China)

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》2018年第1期39-51,共13页Civil Aircraft Design & Research

基　　金：航空科学基金项目(No.20153240003)

摘　　要：在1×106~30×106的雷诺数范围内,马赫数为0.197的情况下,计算并分析了NHLP-2D多段翼型的缝道流动规律,提出了依据缝道出口速度分布定义名义边界层厚度δ/c的方法。研究发现,δ/c随雷诺数的增大而单调减小,且减小速度随雷诺数的增大而明显减缓,符合雷诺数对边界层的影响规律,说明本文定义的δ/c可用于多段翼型边界层厚度的定量研究。对于缝翼缝道,主翼壁面处的δ/c高于缝翼尾缘处的,且二者随迎角的变化规律相反。襟翼缝道处于主翼的强下洗流场中,襟翼上的δ/c随迎角几乎不变。当1×106≤Re≤2×106时,缝道边界层总厚度δT/c随雷诺数有明显的变化,当Re≥3×106时,δT/c随雷诺数的变化率减小。本文研究范围内,δT/c都没有严格地进入雷诺数自准区。当Re≥15×106时,δT/c随雷诺数接近线性变化趋势,为雷诺数规律的外推提供了参考。The slot flow characteristcs of NHLP-2 D multi-element airfoil was calculated and analysed within the Reynolds number range from 1 × 10^6 to 30 × 10^6 and Mach number 0. 197. A nominal boundary layer thickness δ/c was defined according to the velocity distribution at the exit of slot. δ/c decreases monotonically as Reynolds number increases. And the decreasing rate of δ/c also decreases with Reynolds number which is in accordance with the effect of Reynolds number on boundary layer. The δ/c defined here can be used in the quantitative research on multi-element airfoil boundary layer thickness. For the slat slot,δ/c on main element is higher than that on slat trailing edge. And δ/c changes oppositely on the two region. The flow in flap slot is strongly affected by the down wash of main element. As a result,δ/c on flap hardly changes with incidence. At the range of 1 × 10^6≤Re≤2 ×10^6,total boundary layer thickness δT/c changes significantly with Reynolds number. At the range of Re≥3 × 10^6,δT/c decreases slowly with Reynolds number. Within the scope of current study,δT/c does not enter the prospective area of Reynolds number. The δT/c shows a linear reduction with Reynolds number as Re≥15 × 10^6 which provides reference for extrapolation of Reynolds number effect.

关 键 词：增升装置 缝道流动 边界层 雷诺数 数值模拟 

分 类 号：V224.5[航空宇航科学与技术—飞行器设计]