Numerical investigation of airfoils aerodynamic performances

In this study, the aerodynamic performance of seven different airfoils named CLARK Y, YH, Curtis C-72, FX 66-S-196 V1, NACA4412, NACA4415, and NACA4418 was numerically investigated under angles attack ranging from 0° to 30° in increments 5°. 2D (two-dimensional) CFD (Computational Fluid Dynamics) models were created performed steady-state conditions. When changes lift coefficient drag with examined, it observed that increased increasing angle attack. On other hand, firstly then decreased a little remained constant. For all airfoils, value is calculated be highest around 10 15°. The obtained results numerical simulations also analyzed by using GRA (Grey Relation Analysis) method. While determining best method, “higher better” “lower normalization processes used for coefficient, respectively. As result analysis made results, seen worst performances presented C-72 Clark Y airfoil profiles at 10° condition, 15° higher conditions, YH profiles, model velocity distribution compared models.