Güler, EmreDurhasan, TahirKarasu, İlyasAkbıyık, Hürrem2025-03-172025-03-1720212146-05742536-4618https://doi.org/10.21597/jist.897982https://search.trdizin.gov.tr/tr/yayin/detay/468833https://hdl.handle.net/20.500.13099/1090In this study, aerodynamic capabilities of NACA 0018 airfoil is numerically investigatedby installing riblet on the suction side of airfoil. Numerical results were obtained by ANSYS Fluentusing k-kl-kw transition model at Reynolds number of Re=100 000. Three different riblet airfoilconfiguration was performed at six different angles of attack (α=8°, 10°, 13°, 15°, 17° and 19°) andthese results compared with the clean model. For M1 model the riblet was located at chord wise sectionof x/c=0.3 while it installed at x/c=0.7 for M2 model. For M3 model two riblets were used and theywere located at both x/c=0.3 and x/c=0.7. Obtained numerical result show that the use of ribletremarkably affects the flow characteristics of airfoil. At α=8° the CL/CD value of M1 model is increasedby 4.5% when compared to clean model. It is indicated that angle of attack at α=10o , lift coefficient isincreased for all models with compared to clean model. Stall angle is delayed from α=13° to α=15° atM1 and M3 with compared to clean model and lift coefficient is increased about 37% because of therestriction of the laminar separation bubble and trailing edge separation.eninfo:eu-repo/semantics/openAccessMühendislikHava ve UzayArticle10.21597/jist.89798211322082217468833