Experimental Investigation of Pressure Analysis on NACA 2418 Airfoil Across Varying Angles of Attack
This project aimed to experimentally determine the pressure distributions over the NACA 2418 which is a low-camber airfoil. A test airfoil was designed to have six pressure taps on the top surface that are collinear with six pressure taps on the bottom surface. Measurements were taken in the AEROLAB Educational Wind Tunnel set to 40 miles per hour with the airfoil angled at 0°-12°. A custom manometer setup was manufactured to measure the pressure at three points on the airfoil. Increasing the angle of attack resulted in increased pressure differentials between the top and bottom surfaces. The lift force was determined from the observed pressure differentials. Increasing the angle of attack increased the pressure differentials and the lift force.