The key parameters in the wind turbine blade performance are lift and drag coefficient. To economically produce the maximum power by using wind turbines the aerodynamic parameters of the blade profile must be assessed. Even though we have various renewable energy sources, Wind energy has become one of the key solutions to the prevailing energy crisis. At last, some conclusions have been drawn after analyzing the drag of all the profiles at different Reynolds's Number.Ī clean, fuel-free source of the energy wind turbines obviously create energy without generating the damaging pollutants that result from burning coal, gas and other fossil fuels. The cambered aerofoil has provided the least drag and the spherical ball has provided the maximum drag among all the profiles. All the four objects have been tested at 10m/s, 15m/s, 20m/s, 25m/s and 30m/s velocities respectively. The two aerofoils (symmetrical NACA 0015 and cambered NACA 4415) have been tested from-3˚to 18ångles of attack with 3˚steps and spherical ball, cylindrical shaped profiles have been tested from 0˚to 180ångles with 10˚steps at different Reynolds Number. The four different types of objected has been tested at a sub-sonic wind tunnel and experimental data has been obtained at different Reynolds's Number and angle of attack.
This investigation deals with the drag analysis of four different profiles, which are cylinder, sphere, symmetrical aerofoil (NACA 0015) and cambered aerofoil (NACA 4415) objects of same volume. The amount of drag produced significantly depends on shape. Compared to standard NACA 0015 airfoil, a significant improvement in the lift coefficient for multi-element NACA 0015 was noticed especially at the angle of attack (6°,14° and 18°) while slight improvement was noticed in the lifting coefficient for the other two models (bumps NACA 0015, and a backward-facing step NACA0015) at AOA 14 degree. As a result, the geometrical modification influences on the aerodynamic properties of NACA 0015 was investigated.
NACA 0015 SOFTWARE
The CFD software ANSYS FLUENT version 17.1 was used for the computations in the present study. Case II: the coefficient of pressure, coefficient of lift, the contour of static pressure, and the velocity contour for standard NACA 0015(chord length c=1m) were calculated and compared with three geometrical modifications NACA 0015 airfoil. Case I: the numerical analysis method data for the coefficient of lift of standard NACA 0015 (baseline case study) is compared to the previous experimental data. The research focuses on two cases (at different attack angles from 0 to 18 degrees with Re=1.65x10 6). Using SST (Shear Stress Transport) turbulence model and compared with standard NACA 0015 was the performed methodology. The study was performed by simulating three geometrical modification airfoils (bumps NACA 0015, multi-element NACA 0015, and a backward-facing step NACA0015). The airflow around two-dimensional standard NACA 0015 airfoil effect was studied and analysed.
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