Aerodynamic characteristics of NACA 0012 vs. NACA 4418 airfoil for wind turbine applications through CFD simulation

Impact Tip Speed Ratio in Performance Analysis for Horizontal Axis Wind Turbine (HAWT) with Optimal Twist and Tapered (OPT) Blade Shape

“…The first figure provides information about the chamber percentage, and the second digit includes information about the maximum camber along the foil chord. In contrast to chord length, numbers three and four have chord thickness [22]. The NACA 4418 airfoil shows that it has a chamber percentage of 4% and can reach a maximum chamber of 40%.…”

“…The NACA 4418 was employed in this study, with a maximum lift-to-drag ratio of 44.447, which equates to an angle of attack of 6.5° and a lift coefficient of 1.209. The National Advisory Council for Aeronautics (NACA) develops airfoil profiles by assigning a numerical code to the cross-section after assessing its attributes and the letters NACA [22]. Different regulations are used for symmetric and chambered airfoils; for symmetry, the code is NACA 00xx, where xx is the chord thickness ratio [22].…”

“…The National Advisory Council for Aeronautics (NACA) develops airfoil profiles by assigning a numerical code to the cross-section after assessing its attributes and the letters NACA [22]. Different regulations are used for symmetric and chambered airfoils; for symmetry, the code is NACA 00xx, where xx is the chord thickness ratio [22]. NACA 0012, for example, represents a chord whose thickness is 12% of its length [22].…”

“…Different regulations are used for symmetric and chambered airfoils; for symmetry, the code is NACA 00xx, where xx is the chord thickness ratio [22]. NACA 0012, for example, represents a chord whose thickness is 12% of its length [22]. The most straightforward asymmetric system is used by chambered airfoils, which use the asymmetric 4-digit NACA.…”

“…The NACA 4418 airfoil shows that it has a chamber percentage of 4% and can reach a maximum chamber of 40%. The maximum chamber is 40% with 0018 symmetry of thickness 185 of the chord length, and the chamber percentage has a specific meaning on the first digit [22]. Figure 2 depicts the formation of the airfoil profile.…”