Results suggest that the modified airfoil model gives a better performance with an increase of turbulence. The airfoil was designed in the environment of Solidworks, and the CFD analysis was conducted in ANSYS Fluent environment. The considered Reynolds numbers were 6 × 10 4, 6 × 10 5 and 6 × 10 6. Grid files: Grid files for both configurations. Laminar and turbulent as well as incompressible and compressible flow conditions are considered for the current study. Two configurations(0.0 and 4.0 degree angles of attack) were run for the NACA 2412 airfoil geometry. This paper considers a modified version of the NACA 2412 airfoil which has a sinusoidal leading edge as well as an outward dimpled upper surface and evaluates the performance of this modified airfoil with the change of Reynolds number at a different angle of attacks using CFD analysis. From the figure estimate the lift and moment about the quarter chord (per unit span). Literature also suggests that utilization of dimpled surface can improve airfoil performance. Consider the data for the NACA 2412 airfoil given in the figure below. Literature suggests that using protuberances along the leading edge can improve airfoil performance remarkably.
#Naca 2412 airfoil code#
Airfoils have numerous practical applications in the field of aerodynamics, which is why many efforts have been given to improve the performance of the airfoils. NACA 4412 Airfoil 4 digit code used to describe airfoil shapes 1st digit - maximum camber in percent chord 2nd digit - location of maximum camber along chord line (from leading edge) in tenths of chord 3rd and 4th digits - maximum thickness in percent chord NACA 4412 with a chord of 6 Max camber: 0.24 (4 x 6) Location of max camber: 2.4 aft of leading edge (0.
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