摘要
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.
Slot tests on a high lift configuration model of an airplane are completed in the 4m×3m low speed wind tunnel.Different overlap/gap settings of slat and trailing edge flap are evaluated on a semi-span wing/body configuration.The tests show the effects of slot and deflector angle of slat and trailing edge flap on aerodynamic performance and the optimum take-off and landing configurations are acquired.With decreasing the deflector angle of trailing edge flap,three results occur for the take-off configuration,lift-to-drag ratio increases when lift coefficient is fixed or attack angle is large,and it decreases at a small attack angle.For the landing configuration,with the position of slat being varied,the effect of deflector angle of slat on the trends of the maximum lift coefficient and stall angle convert.When the deflector angle increases continually,lift coefficient and the maximum CL declines,while the stall angle rise.
出处
《复旦学报（自然科学版）》
CAS
CSCD
北大核心
2012年第4期415-420,431,共7页
Journal of Fudan University：Natural Science
基金
上海市博士后资助计划重点项目(B)类基金资助(10R21421500)
中国商用飞机有限责任公司博士后基金资助(SR2010003)
关键词
民用飞机
增升装置
风洞试验
缝道
偏度
airplane
high lift configuration
wind tunnel tests
slot
deflection angle
