5. Conclusion

The airfoil optimization using GA for higher aerodynamic efficiency and larger laminar boundary layer is achieved. Furthermore, the turbine power performance increment and air flow visualization of reduced stall from the optimized airfoil are proven via simulation. The higher GR and transition point values due to the reduced drag from expanded laminar boundary layer region are presented for the optimized airfoil. The boundary layer characteristics such as diminished skin-friction coefficients and higher transition point values over all flow regimes are found to be the reason behind the improved aerodynamics of the optimized airfoil. The results present the contribution of specifically airfoil shape for aerodynamic efficiency and modified boundary layer distribution on HAWT performance improvement including an effective lifting of the blades and rotor rotation.
