NACA 0009 Profilli Bir Kanadin Düşük Bir Reynolds Sayisinda Had Analizi

Abstract

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