Numerical and experimental study of NACA airfoil in low Reynolds numbers for use of Darriues vertical axis micro-wind turbine

The three low Reynolds number airfoils, NACA0015, NACA0018, and NACA0021, were examined. First, CFD and experimental testing were done in the wind tunnel using the numerical Vortex-Blade method, and it was used for the panel method of the KW-SST model. The findings demonstrated that the Reynolds numbers are more affected by airfoils when there are two airfoils present, as opposed to when there are more than two. The segmentation coefficient has been used to remove the tip radius and lift coefficient in the angle of attack less and less than other methods, according to comparison and results that showed that the method of vortex shedding and lift coefficient ratios in angle of attack between 10º and 18º in the laboratory were analyzed. In the attack angle of 10° and CFD model with a 1.8 and 2.3% error rate, increasing the attack angle of the CFD model, and Fortran at an attack angle of 18° with the 4 and 5.2% Fortran model and at the top of the CFD model for the analysis.