Abstract
The current work aims to increase the NACA 1410 airfoil's aerodynamic efficiency by altering its surface qualities for various angles of attack. The NACA 1410 airfoil's lower surface has semicircular outward and inward protrusions for a more advantageous profile. The lift and drag coefficients were calculated using CFD, at various attack angles, from -2º to 18º. An ANSYS Fluent Workbench model of the NACA 1410 airfoil was used to investigate flow characteristics at 3 x 105 Reynolds numbers. The semicircular protrusions caused turbulence, reducing pressure drag and increasing lift, delaying flow separation. The NACA1410 profile has protrusions facing outward, increasing the pitch moment coefficient. The inward protrusion was found to be more advantageous in the study of the effects of surface alterations on airfoils at various angles of attack.
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