摘要
在哈尔滨气动院FL-9增压风洞进行了某大型客机低速高雷诺数半模测力测压风洞试验,来流马赫数为0.2,增压范围为1~4个大气压。基于模型机翼平均气动弦长的雷诺数从2.9×106到11×106。以此为基础主要分析了雷诺数对机翼纵向气动力特性的影响,结果发现雷诺数对升力线斜率、最大升力系数、失速攻角和失速特性都有影响。相对于增升装置打开后的高升力构型,雷诺数对巡航构型的影响更明显。
Aerodynamic characteristics for a large civil aircraft are experimentally investigated at FL- 9 low speed pressurized wind tunnel,focusing on the effect of Reynolds Number. The flow Mach number of 0. 2 and the pressure range of 1 ~ 4 atmospheric pressure are adopted in this test. The Reynolds number based on the model mean aerodynamic chord and free- stream velocity is from 2. 9 × 10~6 to 11 × 10~6. Longitudinal aerodynamic characteristics of the wing are mainly analyzed. The experimental results show that the lift curve gradient,the maximum lift coefficient and the stalling angle of attack are all affected by Reynolds Number. Compared to the high lift configurations,the effect of Reynolds number on cruise configuration is more obvious.
出处
《民用飞机设计与研究》
2016年第1期45-47,88,共4页
Civil Aircraft Design & Research
关键词
雷诺数
大型客机
升力系数
低速
迎角
reynolds number
large civil aircraft
lift coefficient
low speed
angle of attack
