Comparison of aerodynamic performances of various airfoils from different airfoil families using CFD
Küçük Resim Yok
Tarih
2021
Yazarlar
Dergi Başlığı
Dergi ISSN
Cilt Başlığı
Yayıncı
Techno-Press
Erişim Hakkı
info:eu-repo/semantics/closedAccess
Özet
In this study, three airfoil families, NACA, FX and S, in each case three from each series with different shapes were investigated at different angles of attack using Computational Fluid Dynamics (CFD) method. To verify the CFD model, simulation results of the NACA 0012 airfoil was compared against the available experimental data and k-omega SST was used as the turbulence model. Lift coefficients, lift to drag ratios and pressure distributions around airfoils were obtained from the CFD simulations and compared each other. The simulations were performed at three Reynolds numbers, Re=2x10(5), 1x10(6) and 2x10(6), and angle of attack was varied between -6 and 12 degrees. According to the results, similar lift coefficient values were obtained for symmetric airfoils reaching their maximum values at similar angles of attack. Maximum lift coefficients were obtained for FX 60-157 and S 4110 airfoils having lift coefficient values around 1.5 at Re=1x10(6) and 12 degrees of angle of attack. Flow separation occurred close to the leading edge of some airfoils at higher angles of attack, while some other airfoils were more successful in keeping the flow attached on the surface.
Açıklama
Anahtar Kelimeler
Aerodynamics, Airfoil, Cfd, Naca Series, Fx Series, S Series
Kaynak
Wind And Structures
WoS Q Değeri
Q3
Scopus Q Değeri
Q3
Cilt
32
Sayı
3
