A. Yadav, Dhruv P. Suthar, Hetal Bhatiya, Aniruddh Marakana, Mohammad Shadab Ghanchi, Sathish Dharmalingam
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Experimental Investigations on Aerodynamic Performances of NACA0012 Airfoil
The aerodynamic characteristics for the various angles of attack at different Reynolds numbers with a view to extending the knowledge of the pressure distribution over the NACA 0012 airfoil have been measured in a low-speed subsonic wind tunnel. Experiments were carried out by varying the angle of attack from −30 to +30 degrees and the velocity varied from 10 m/s to 25 m/s. The lift coefficient and drag coefficient for the NACA 0012 airfoil are obtained by measuring the pressure distribution from the pressure ports situated over the airfoil surface.
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