Comparative Numerical Study of NACA0010 and NACA0021 at Various Angles of Attack
7 Pages Posted: 12 Feb 2018
Date Written: December 21, 2017
In present work, an attempt is made to identify the comparative numerical study of NACA0010 and NACA0021 to investigate the coefficient of lift and drag at various angles of attack. The results shown here are for every two degree of angles of attack between 0 o to 10o by computational fluid dynamics analysis. The validations of the present work are done on ANSYS-15(FLUENT) software by comparing the results obtained by UIUC Airfoil coordinate database. It has been observed that the present results are closely matching with the UIUC Airfoil coordinate database. These analyses are done at same Reynolds number (Re) for both NACA0010 and NACA0021. It has been found that NACA0010 shows good characteristics comparatively at different angles of attack under steady flow condition.
Keywords: Airfoil, Lift and Drag, Reynolds Number, Angle of Attack
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