Investigation of a Rib Structure Effect on the Aerodynamic Performance of a Plain Flapped Symmetrical Airfoil

In this paper, two-dimensional computational fluid dynamics analyses were conducted to examine the rib effect on performance of NACA 0018 plain flapped airfoil. A mesh independence study was carried out and Spalart-Allmaras turbulence model selected for validation. Four various airfoil models designed: M1 (airfoil without flap structure), M2 with M3 a flap) M4 structure flap). The designed airfoils calculated in terms lift-to-drag (C_L/C_D) ratio. As result, significantly increased lift coefficient (C_L) drag (C_D). While enhanced aerodynamic non-flapped when attack angle greater than 12°, it at almost all angles. Furthermore, seen that decreased C_D values angles C_L 2°.