الفهرس 
INTRODUCTIONOnly 14 pages are availabe for public view
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Abstract
The airfoil is one of the most essential components that have a great influence on wind turbine
performance. The present research starts with a numerical investigation of the impact of the trailing
edge design for the 2D NACA 0012 on airfoil performance. The design and simulation are
conducted by computational fluid dynamic (CFD). The influence of various relative thickness and
relative bluntness ratios of the trailing edge on the lift/drag ratio and lift coefficient is studied. The
optimized design of the thick trailing edge is compared with the optimized blunt trailing edge
airfoil. The results show that the thick trailing edge gave a higher performance. After that, the
trailing edge of the optimized thick trailing edge is inclined to various angles to achieve further
improvement in the lift/drag ratio and lift coefficient. The results reveal that all the designed
airfoils demonstrated higher lift coefficients when compared with baseline airfoil. The maximum
lift coefficient improvements of the blunt airfoil, thick airfoil, and inclined airfoil are 27.7%,
31.17%, and 74%, respectively. In addition, the maximum optimized glide ratios of the blunt
airfoil, thick airfoil, and inclined airfoil are 6%, 10.794%, and 39.495%, respectively. The
influence of adding a different flap length to the 2D SD8000 airfoil is studied. We use relative
Reynolds numbers with the constant chord length of the airfoil. The results show an increase in
the maximum value of lift coefficient and lift/drag ratio due to the use of flap at a low Reynolds
number. Then, add an extended flap for each 2D element of the rotor blade individually. The results
show, as compared to the baseline airfoils, an improvement in lift coefficient at the low tip speed
ratio. Finally, add the different lengths of the flap (10%c and 20%c) on the whole 3D blades of the
rotor. The results also show the improvement in power coefficient at low tip speed ratio when
compared with baseline rotor. The maximum value of power coefficient is achieved at tip speed The airfoil is one of the most essential components that have a great influence on wind turbine
performance. The present research starts with a numerical investigation of the impact of the trailing
edge design for the 2D NACA 0012 on airfoil performance. The design and simulation are
conducted by computational fluid dynamic (CFD). The influence of various relative thickness and
relative bluntness ratios of the trailing edge on the lift/drag ratio and lift coefficient is studied. The
optimized design of the thick trailing edge is compared with the optimized blunt trailing edge
airfoil. The results show that the thick trailing edge gave a higher performance. After that, the
trailing edge of the optimized thick trailing edge is inclined to various angles to achieve further
improvement in the lift/drag ratio and lift coefficient. The results reveal that all the designed
airfoils demonstrated higher lift coefficients when compared with baseline airfoil. The maximum
lift coefficient improvements of the blunt airfoil, thick airfoil, and inclined airfoil are 27.7%,
31.17%, and 74%, respectively. In addition, the maximum optimized glide ratios of the blunt
airfoil, thick airfoil, and inclined airfoil are 6%, 10.794%, and 39.495%, respectively. The
influence of adding a different flap length to the 2D SD8000 airfoil is studied. We use relative
Reynolds numbers with the constant chord length of the airfoil. The results show an increase in
the maximum value of lift coefficient and lift/drag ratio due to the use of flap at a low Reynolds
number. Then, add an extended flap for each 2D element of the rotor blade individually. The results
show, as compared to the baseline airfoils, an improvement in lift coefficient at the low tip speed
ratio. Finally, add the different lengths of the flap (10%c and 20%c) on the whole 3D blades of the
rotor. The results also show the improvement in power coefficient at low tip speed ratio when
compared with baseline rotor. The maximum value of power coefficient is achieved at tip speed ratio 3 and rotor with flap 20%c. This study contributes toward the design of efficient wind
turbines.