NACA 0009 Profilli Bir Kanadin Dü?ük Bir Reynolds Sayisinda Had Analizi

Proper blade design, selection and use continue to gain importance with the developing technology, aviation space industry. Many applications wings such as aircraft (planes, helicopters, etc.), UAV (Unmanned Aerial Vehicle), wind turbines so on. This study covers a NACA 0009 profiled wing 111 mm span chord its CFD analysis using Ansys version 15.0. Three-dimensional has been done Fluent. A geometry was created, this meshed properly, tighter especially close wings, completed k-w turbulence model. In total 2,078,272 nodes 2,036,295 elements have formed in mesh. Four different angles of attack tested which are 0°, 5°, 10° 15° at 37,000 Reynolds number. Generated mesh an average skewness rate 1.3 orthogonal quality 0.97. Velocity contours streamlines compared literature. Lift drag coefficients monitored. As angle increases, it is seen that shocks form trailing edge therefore aerodynamic performance tested. With L/D ratio 10.03, 5° prevailed comparisons.