Soğukpınar, HacıBozkurt, İsmail2018-12-112018-12-112015-06-112149-01042149-5262https://hdl.handle.net/11363/489DOI: 10.19072/ijet.105718In this paper, aerodynamic performance of airplane NACA 2415 airfoils were numerically investigated to understand effect of angle of attack on the aerodynamic performance. The lift and drag coefficient, lift to drag ratio and power coefficients around NACA 2415 aerofoil were calculated with SST turbulence model and are compared with two different experimental data to validate simulation accuracy of Computational Fluid Dynamics approach. Result indicates that at the low angle of attack, the lift coefficient of NACA 2415 aerofoil obtained in the present study is in a good agreement with experimental results but after zero degree agreement is not good with experimental results.eninfo:eu-repo/semantics/openAccessResearch Subject Categories::TECHNOLOGYArticle