Akademik Veri Yönetim Sistemi
JOURNAL OF POLYTECHNIC-POLITEKNIK DERGISI, cilt.27, ss.967-974, 2024 (ESCI)
In this paper, two-dimensional computational fluid dynamics analyses were conducted to examine the rib effect on the performance of the NACA 0018 plain flapped airfoil. A mesh independence study was carried out and the Spalart-Allmaras turbulence model was selected for validation. Four various airfoil models were designed: M1 (airfoil without plain flap and rib structure), M2 (airfoil with rib structure), M3 (airfoil with a plain flap) and M4 (airfoil with a rib structure and plain flap). The performance of designed airfoils was calculated in terms of lift-to-drag (CL/CD) ratio. As a result, the plain flap significantly increased the lift coefficient (CL) and drag coefficient (CD). While the rib structure enhanced the aerodynamic performance of the non-flapped airfoil when the attack angle was greater than 12 degrees, it increased the performance of the plain flapped airfoil at almost all attack angles. Furthermore, it was seen that the rib structure decreased CD values of plain flapped airfoil at all attack angles and increased CL values of plain flapped airfoil when the attack angle was greater than 2 degrees.