Axial Velocity in the Trailing Vortex Core of a NACA 0015 Airfoil

Summary of research performed on a NACA 0015 airfoil in USU’s low speed windtunnel to validate parameters derived by Spalart, which relate the circulation strength with the relative axial velocity of the core. Experiments were performed for several Reynolds numbers and angles of attack at a distance of 1 chord length from the trailing edge of the airfoil. Data was collected using a triple sensor hot-wire anemometer to allow resolution of the velocity into three orthogonal components