Iranian Society of Heating, Refrigerating, and Air Conditioning Engineers (IRSHRAE) Journal of Renewable and New Energy 2423-4931 10 2 2023 09 23 Numerical and experimental study of NACA airfoil in low Reynolds numbers for use of Darriues vertical axis micro-wind turbine Numerical and experimental study of NACA airfoil in low Reynolds numbers for use of Darriues vertical axis micro-wind turbine 149 163 169628 10.52547/jrenew.10.2.149 FA Hossein Seifi Master of Mechanical Engineering, Department Marine of Engineering, Chabahar Maritime University, Chabahar, Iran 0000-0003-3905-8739 Shahriar Kouravand Associate Professor, Mechanical Engineering, College of Abouraihan, University of Tehran, Tehran, Iran Mohsen Seifi Davary Master Civil Engineering Student, Islamic Azad University- Germi Branch, Germi, Iran 0000-0002-9323-3983 Journal Article 2020 09 06 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. 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. https://www.jrenew.ir/article_169628_41d6467b4a69d31dbdd143dd2fba669c.pdf