In this study, the objective is to investigate the effect of aerodynamically shaped vortex generators (VGs) on the tapered swept-back NACA 0020 airfoil having sweep angle of 25⁰. The dimensions of the VGs were chosen as l = 15 mm, h = 5 mm, d = 5 mm, λ = 35 mm and β = 13°. Force measurements were carried out at angles of attack between 0° and 30° with an increment of 1⁰ for Reynolds number of 6×104. Experiments were first conducted without VGs, then wing model with the VGs was placed in five different positions (XVG/c=0.1, 0.2, 0.3, 0.4, 0.5). Results showed that VGs delayed the stall angle by 2⁰, 2⁰ and 1⁰ at XVG/c=0.1, XVG/c=0.3 and XVG/c=0.4 positions, respectively. When it compared with the baseline airfoil model, there was a 7% increase in maximum lift coefficient (CLmax) at the position of aerodynamically shaped VGs at XVG/c=0.1. The baseline model has lower drag coefficient (CD) values at all angles of attack than the models with VGs. The model with VG at XVG/c=0.1 was improved the CD as compared to the baseline and the other models at 15⁰ ˂ α ˂ 23⁰. The results indicates that the VGs placed at XVG/c= 0.2, 0.3, 0.4, 0.5 did not improve the aerodynamic performance of the tapered swept back NACA 0020 airfoil model in general, only the 10VGβ13λ35 outperformed the baseline model. ORCID NO: 0000-0002-5927-9128
Anahtar Kelimeler: Aerodynamically shaped vortex generators, tapered swept-back NACA 0020, Lift coefficient, Drag coefficient, Lift to drag coefficient
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