民用飞机前缘缝翼气动力特性SCCH试验研究

摘要

针对民用飞机增升装置对机翼气动力特性的影响,在南京航空航天大学NH-2低速风洞开展了某型号客机等弦长后掠半模(Swept constant chord half-model,SCCH)增升装置测力风洞试验研究.试验来流马赫数为0.2,基于机翼弦长的试验雷诺数为1.85×106.通过试验结果,重点分析了前缘缝翼的偏角、缝道宽度及缝道搭接量对机翼增升装置增升效率的影响,得到了起飞构型和着陆构型缝翼偏角及缝道的最佳组合参数.试验研究发现,缝翼偏角从18°增加到24°时,失速迎角和最大升力系数都增大,缝翼偏角从25°增加到31°时,失速迎角增大,最大升力系数没有明显的变化.起飞构型前缘缝翼最佳缝道宽度为1.5％～2.0％,最佳缝道搭接量为1.0％左右;着陆构型缝翼最佳缝道宽度为2.0％～2.5％,最佳缝道搭接量为-1.0％～0％.最佳缝道宽度随缝翼偏角的增加呈现增大趋势.%Focusing the influence of high-lift configuration of an airplane on wing aerodynamic characteristics,an experiment is conducted in NH-2 low-speed wind tunnel over a swept constant chord half-model (SCCH)high-lift configuration of a civil aircraft.In this experiment,the Mach number is 0.2 and the Reynolds number is 1.85×106.The effect of salt deployment angle,gap and over-lap on efficiency of high-lift configuration is investigated.Based on the test results,best slat parameters of this model are obtained for both take-off and landing configurations.The results show that both the stall angle of at-tack and the maximum lift coefficient increase with the slat deployment angle increasing from 18°to 24°, and only the stall angle of attack increases while the maximum lift coefficient does not change obviously when the angle increasing from 25°to 31°.The best slat gap width is from 1.5％ to 2.0％ for take-off configuration,while 2.0％ to 2.5％ for landing configuration.The best over-lap is around 1.0％ for take-off configuration,while -1 .0％ to 0％ for landing configuration.The best slat gap width presents increasing trend with the increase of the slat deployment angle.