论文部分内容阅读
针对民用飞机增升装置初步设计阶段的起飞和着陆构型进行了缝道试验研究,比较分析了前缘缝翼、后缘襟翼偏度和位置参数对增升装置气动性能的影响,得到了前后缘缝道和偏度最佳组合参数.试验研究发现,该模型在起飞状态下,后缘偏度越小,极曲线特性越佳,且在小迎角范围内,升阻比随后缘偏度减小而降低,在迎角较大时则相反变化.对于着陆构型,前缘偏度对CLmax和失速迎角影响的趋势会随着前缘位置变化而发生改变;当后缘偏度增大时,着陆构型的升力系数和CLmax会减小,失速迎角增大.
Aiming at the take-off and landing configuration of the initial design stage of the civil aircraft lifting device, the seam test was conducted. The influence of the leading slat, trailing edge flap deviation and position parameters on the aerodynamic performance of the lifting device was analyzed. The best combination parameters of front and rear seam and skewness.Experimental study found that the smaller the trailing edge deviation, the better the characteristic of the polar curve in the take-off state, Degree decreases and decreases when the angle of attack is larger.For the landing configuration, the tendency of leading edge skewness to CLmax and stalling angle of attack will change with the change of leading edge position. When trailing edge skewness As it increases, the lift coefficient and CLmax of the landing pattern decrease and the angle of attack at attack increases.