ME6121 - Aerofoil Pressure Distribution in Wind Tunnel Testing

This report details an experiment on aerofoil pressure distribution using a NACA 653-418 aerofoil in a wind tunnel. The experiment involved measuring pressure at various points on the aerofoil at different angles of attack, and then calculating the pressure coefficients. The results are presented in tables and graphs, showing the pressure distribution and lift coefficient. The report discusses the effect of angle of attack on pressure distribution and lift, and compares the experimental results with literature. Alternative flow visualization techniques like hydrogen bubble visualization, dye visualization, Schlieren photography, and smoke visualization are explored, along with a discussion on underbody tunnels and a case study of open-wheel race car wing design. The slowing point for the aerofoil contemplated is around 12.5°; this implies past this approach no more lift can be created because of the stream partition that happens on the upper surface of the aerofoil.