The boundary layer and aerodinamic analyisis of NACA 0012 airfoil in wind tunnel

In the light of results of the thesis, low Re numbered around wing profiles is examined pressure and speed change of air-flow. Wind tunnel and design parameters of airfoil of Naca0012 is determined and it is intended to obtain aerodynamic principles by courtesy of fluent sowftware package. The values of pressure are measured to control whether the wind tunnel is suitable for analysis without any model in the tunnel. The values of pressure are changed value of speed with helping Bernoulli Equation. .Analysis of airflow is shown in graphs. As a result in graphs, testable model and convenience of calibration tunnel are presented in wind tunnel. As a result in graphs, testable model and convenience of calibration tunnel represented in wind tunnel. Wing of Naca0012 is placed in an empirical calibration the wind tunnel as a model, boundry conditions of airfoil profile are determined by supporting simulated sowftware GAMBIT and it is used 5000 cells to obtain the best solution. An independence structure of network is far from parameters is created via determining structure of network in Fluent programme. It is used Realizable k-εw which is a turbulence similarity model. Test section channel and NACA 0012 wing 2 degrees, 4 degrees and 6 degrees angle of attack in the boundary layers interact with each other and which and analysis are not suitable for speeds at which point in the boundary layer at the intersection of spots is determined. The air velocity in the test section of the wind tunnel 0,1 m / s while the intersection of the boundary layer is demonstrated graphically. In speed of the value of the selected, 3,4 m/s, 5,9 m/s and 15 m/s (Re=0,35*〖10〗^5) , (Re=0,609*〖10〗^5 ) , (Re=1,548*〖10〗^5) speed values 2^0 degrees, 4^0 degrees and 6^0 degrees angle of attack in the static pressure contours is examined visually. Pressure differences is examined, pressure coefficients graphically revealed. The pressure coefficient distribution graph obtained from the solution according to the angle of attack increases when the pressure difference above and below the blades are increased. The lift force caused by the pressure difference is in agreement with the literature review.