Investigation of low reynolds number air and water flow over blade profile with slat and aerodynamic performance analysis

As a result of the developments and the difficulties that has been faced on wind turbines, the aerodynamic researches in recent years concantrates on low Re number flow contol and high lift production. As traditionally, in the world, standart turbine airfoils are used for generating energy. Provided that the maximum lift coefficient is around 1.6. By using these turbines airfoil, minimum required wind speed is 7 m/s for generating energy. In this thesis, numerical investigations related with these subjects are presented and reveal that a wind turbine blade profile which can provide high performance and produce electric energy from hydrokinetic energy with use this profile. Before starting numerical studies, NACA 2415 that is going to be used as airfoil profile and the NACA 22 that is planned to be connected to this as a slate profile are determined. Firstly, in terms of time and budget,dimensional analysis was made that benefits our task and determined our dimensional parameters. Later, optimum number of network is calculated in the numerical studies which are going to be studied to make calculations regardless of the number of cells. Fine mesh is used with 55000 cells in GAMBITTM program to get the most correct result. In numerical solutions derived with FLUENTTM program at different distances between slat and airfoil, different angles of attack and angle of slats and different Re numbers In air an water conditions. NACA2415 without slat blade profile?s without slat,numerical solutions were compared with this numerical solutions which examined under the same conditions. Later on, with and without slat Naca 2415 wing profile that is set in flow circumstances, the changes in 1x10^5 Re number in water flow and 2,53x10^5 Re number in water flow and Cl-Cd factor in different attack angels are investigated. They are compared with the experimental studies in the literature to be sure about the accuracy of proximity of the rates. , with and without slat wing profile?s pressure contours, pressure coefficient, distribution, velocity contours, steam lines, turbulence intensity and frequency of vortex break are identified in attack angels that includes max. CL and CL/CD rates. In a result of all numerical evaluations, wing?s attack and slate angels that had to be done in water and air conditions are determined. Obtained the optimum blade?s twist angle, which is changing with tip speed ratio, with used blade element momentum theory. In air flow, while the distance between the blades h/c1=0.165 and 1x10^5 Re number, the maximum lift coefficient as obtained 2.46 at 27 attack angle. But, CL/CD ratio is more important to provide maximum power coefficient and blade form is designed according to this ratio. The optimum attack angle was chosen 12. Because, the maximum CL/CD ratio was obtained at this attack angle while the distance between the blades h/c1=0.165 and 1x10^5 Re number. For NACA2415 without slat blade profile, the maximum lift coefficient as obtained 1.02 at 12 attack angle. In water flow, while the distance between the blades h/c1=0.165 and 2.53x10^5 Re number, the maximum lift coefficient as obtained 2.49 at 33 attack angle. But, the optimum attack angle was chosen 10. Because, the maximum CL/CD ratio was obtained at this attack angle while the distance between the blades h/c1=0.165 and 2,53x10^5 Re number. For NACA2415 without blade profile, the maximum lift coefficient as obtained 1.35 at 18 attack angle. As a result of calculations, blade profile?s with slat aerodynamic performance was found to be higher, which is used in air and water flows, according to NACA2415 without blade profile.