带缝翼多段翼型气动特性的实验研究  

Experimental investigation of aerodynamics performance of multi-element airfoil with leading-edge slat

作　　者：惠增宏[1] 竹朝霞[1] 张理[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国家重点实验室,西安710072

出　　处：《实验流体力学》2007年第2期17-20,24,共5页Journal of Experiments in Fluid Mechanics

摘　　要：首先对测力和测压两种翼型的实验方法作了对比研究,在此基础上用测压法对多段翼型前缘缝翼气动特性进行了实验研究。结果表明,测力和测压两种方法均可用于翼型的实验研究,前缘缝翼缝道的不同构型对多段翼型的增升效果和气动效率(升阻特性)都有极大的影响。具有前缘缝翼最佳优化缝道多段翼型的最大升力系数CL max可达3.900,失速迎角α为31°,它比普通缝道多段翼型的最大升力系数(2.790)增加了39%,失速迎角增大了23°。The comparative investigation between the direct measuring method and surface pressure measurement method of the aerodynamics force on airfoil is performed in two-dimensional testing section of NF-3 wind tunnel at Northwestern Polytechnical University; and the experimental investigation of aerodynamics perforrnance of multi-element airfoil with leading-edge slat is carried out. It is shown from result that two experimental method is both able to used in experimental research on aerodynamics performance of airfoil and the gap width of leading-edge slat has great effects on high lift and aerodynamic efficiency. The highest lift coefficient of multi-element with optimum gap width of leading-edge slat increases to 3.900 from 2.790 of multi-element with general gap width of leading-edge slat ; Stall angle up to 31° from 8°.

关 键 词：缝翼缝道 多段翼型 气动特性 风洞 气动力测量 压力测量 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程] V211.74