在民用飞机增升装置低速半模风洞试验的基础上,针对内缝翼和短舱导流片进行了前缘增升装置气动特性试验研究,分析了内缝翼长度对增升装置升力系数的影响,比较了短舱导流片在起飞和着陆状态下的气动特性.试验结果表明,增升装置线性段升力系数不受内缝翼长度的影响,失速区升力系数和CL max随内缝翼长度增加而增大；模型安装短舱导流片后,最大可用升力系数、CL max和失速迎角明显增加,升阻比和俯仰力矩特性在失速区也得到了改善,且线性段气动性能没有发生大的改变.%Aim. The introduction of the full paper discusses recent relevant developments and then proposes the experimental research mentioned in the title, which we believe has shown good promise for further improving high-lift configurations and is fully explained in sections 1 and 2. Their core consists of; (1) we did inboard slat and strake experiments on the high-lift configuration of an airplane model in the 4 m x 3 m low-speed wind tunnel to analyze its aerodynamic performance; ( 2 ) we analyze the effects of different length settings of an inboard slat on the lift coefficient of the high-lift configuration and compare the aerodynamic performances of a nacelle strake during take-off and landing operiations respectively. The experimental results, given in Figs. 4, 5 and 6, and their analysis show preliminarily that; (1) linear lift coefficients of the high-lift configuration does not increase with increasing length of the inboard slat; (2 ) the lift coefficients in stall region and CL max increase with increasing length of the inboard slat; ( 3 ) with the nacelle strake installation, the maximum useable lift, CL max and the stall angle of attack increase significantly the lift-to-drag ratio and the pitching moment coefficient improve remarkably, while the aerodynamic performance of the linear section shows a little change.
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