CAJ | 학술논문

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。
통과수조경기포류동현시화 PIV 측속실험연구료 NACA0012익형재뢰낙수위8200시적류동특성，중점관주료익형요류결구수영각적변화。연구발현：분리점화분리전절층형성선와적위치수영각적증대이향상유이동，동시익형상표면류동분리후형성적회류구척촌수착익형영각적증가이증대。당류동재부우익형상표면시，재재부점부근능구관측도전향와적삼유연화과정，병능관측도전향와적국부배대현상。
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 the roll-up-vortices,as well as vortex par-ing,is observed around the reattachment point.