摘要
通过水槽氢气泡流动显示和PIV测速实验研究了NACA0012翼型在雷诺数为8200时的流动特性,重点关注了翼型绕流结构随迎角的变化。研究发现:分离点和分离剪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型迎角的增加而增大。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。
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.
出处
《实验流体力学》
CAS
CSCD
北大核心
2013年第6期32-38,共7页
Journal of Experiments in Fluid Mechanics
