几种前缘流动控制的实验研究  

EXPERIMENTAL INVESTIGATION OF SEPARATION FLOW CONTROL USING VORTEX-GENERATING DEVICES

作　　者：刘宝杰[1] 杨晓宁[1] 沈遐龄[1] 高歌[1] 

机构地区：[1]北京航空航天大学404教研室,北京100083

出　　处：《工程热物理学报》1998年第4期444-448,共5页Journal of Engineering Thermophysics

基　　金：国防基金

摘　　要：This paper presents the experimental investigations of high angle-of-attack flow con-trol on NACA0012 airfoil using vortex-generating devices in low speed wind tunnel. The vortex-generating devices used are (i) top-surface triangular wing type vortex-generators,(n) leading-edge vortex-generators, (iii) leading-edge slots. Experiment Renolds number range is 4.9×105 to 6.5×105, the angle-of-attack range is -10° to 20°. The comparisons of experimental results show that the vortex-generating devices can dramatically improve airfoil aerodynamic characteristics at normal stall angle-of-attack by increasing both the lift and the lift-to-drag ratio.This paper presents the experimental investigations of high angle-of-attack flow con-trol on NACA0012 airfoil using vortex-generating devices in low speed wind tunnel. The vortex-generating devices used are (i) top-surface triangular wing type vortex-generators,(n) leading-edge vortex-generators, (iii) leading-edge slots. Experiment Renolds number range is 4.9×105 to 6.5×105, the angle-of-attack range is -10° to 20°. The comparisons of experimental results show that the vortex-generating devices can dramatically improve airfoil aerodynamic characteristics at normal stall angle-of-attack by increasing both the lift and the lift-to-drag ratio.

关 键 词：大攻角绕流 分离流控制 涡流发生器 空气动力学 

分 类 号：TK123[动力工程及工程热物理—工程热物理] V211[动力工程及工程热物理—热能工程]