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.
Experimental Investigations on Aerodynamic Performances of NACA0012 Airfoil
2022-07-21
346626 byte
Conference paper
Electronic Resource
English
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