Experimental Investigation of Aerodynamic Coefficients of NACA 4412 Aerofoil

Aerofoils are an integral part of the automobile, aviation, and energy sectors. Thus, it is crucial to analyze the phenomena behind the concept of aerofoil's lift and drag force. The main objective of this work is the fabrication and experimentation of an asymmetric aerofoil. In the present work, experimentation of NACA 4412 aerofoil is done to calculate the performance coefficients at Re = 92,500 (based on chord length) for the angle of attack varying from 0° to 18°. Fabrication of the aerofoil is done using a 3D printer. Polylactic acid (PLA) material is used for 3D printing. The aerofoil model was fabricated with provisions for the pressure taps on both upper as well as the lower surface. The effect of the different angles of attack is studied on lift and drag. The stall angle at which lift is maximized is found to be 15°. The study could be helpful in selecting the optimum angle of attack based on the required application and finding stall angle.