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NACA0012翼型低雷诺数绕流的实验研究
引用本文:吴鋆,王晋军,李天. NACA0012翼型低雷诺数绕流的实验研究[J]. 气动实验与测量控制, 2013, 0(6): 32-38
作者姓名:吴鋆  王晋军  李天
作者单位:[1]北京航空航天大学流体力学研究所,流体力学教育部重点实验室,北京100191 [2]中航工业集团沈阳飞机设汁研究所,沈刚110035
摘    要:通过水槽氧气泡流动显示和PIV测速实验研究了NACA0012翼型在雷诺数为8200时的流动特性,重点炎注了翼型绕流结构随迎角的变化。研究发脱:分离点和分离翦切层形成旋涡的位置随迎角的增大而向上游移动,同时翼型上表面流动分离后形成的回流区尺寸随着翼利迎角的增加而增大。当流动再附于翼型上表面时,在再附点附近能够观测到展向涡的三维演化过程,并能观测到展向涡的局部配对现象。

关 键 词:流动显示  NACA0012翼型  低雷诺数  层流分离泡  水洞实验

Experimental investigation on low Reynolds number behavior of NACA0012 airfoil
WU Jun,WANG Jin-jun,LI Tian. Experimental investigation on low Reynolds number behavior of NACA0012 airfoil[J]. , 2013, 0(6): 32-38
Authors:WU Jun  WANG Jin-jun  LI Tian
Affiliation:1. Institute of Fluid Mechanics, Beijing University of Aeronautics Astronautics, Key I.abora- tory of Fluid Mechanics, Ministry of Education, Beijing 100191, China; 2. AVIC Shenyang Aircraft Design and Research Institute, Shenyang 110035, China)
Abstract:An experimental study on the boundary layer flow and near wake behavior of a NA- CA0012 airfoil was conducted in the water tunnel, with the primary interest in the evolution of coherent structures at different angles-of-attack up to 15° and Reynolds number of 8200. It is found that the separation point, as well as the location of vortex roll up, moves toward the lead- ing-edge of the airfoil as the angle-of-attack increases, and the size of reserve flow region also in- creases as the angle-of-attack increased. When a laminar separation bubble is formed at some an- gles-of-attack, the three dimensional deformation of tile roll-up-vortices, as well as vortex par- ing, is observed around the reattachment point.
Keywords:flow visualization  NACA0012 airfoil  low Reynolds number  laminar separationbubble  water tunnel test
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