论文部分内容阅读
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。
Under the Reynolds number of 1 × 10 ~ 630 × 10 ~ 6 and the Mach number of 0.197, the effect of Reynolds number on the aerodynamic characteristics and flow characteristics of NHLP-2D airfoil was studied by numerical method. The established numerical model considers the grid processing of confluence boundary layer. Comparing with the existing experiments and calculation results, this numerical model is credible. The results show that when the Reynolds number is more than 1.5 × 10 ~ 7, the influence of Reynolds number on the aerodynamic coefficient decreases obviously, and the aerodynamic force changes linearly with the Reynolds number at low angle of attack. The height of confluence boundary layer decreases with increasing Reynolds number, and the wake strength produced by slat and main wing weakens with the increase of Reynolds number, and the width of wake decreases gradually. At high Reynolds number, there is still a strong slat trail at the tail edge of the flaps, indicating that the wake / boundary layer fusion decreases with increasing Reynolds number. This paper provides the basis for the study of the effect of subsequent Reynolds numbers on the flow characteristics of the slits.