Aerodynamic analysis of NACA 0008 wing profile with force and flow visualization in subsonic wind tunnel

In this study, force changes and flow visualization studies around the airfoils of low Reynolds number airflow were examined. The design parameters of the "NACA 0008" wing were determined in the open-loop subsonic wind tunnel located in the Wind Tunnel Laboratory of the Mechanical Engineering Department of Kütahya Dumlupınar University and it was aimed to obtain aerodynamic analyzes using the Ansys Fluent package program. Force analysis of the "NACA 0008" wing structure was performed at certain speeds. Force analyzes were carried out at 6x10⁴, 8x10⁴ and 10x10⁴ Reynolds number values and measurements were carried out in 2° increments of the angle of attack starting from 0° to 18°. Lift and drag coefficients were determined by force measurements. When the graphs obtained from these coefficients were examined, it was determined that the "NACA 0008" wing structure lost adhesion at 6°. Flow visualization study was carried out with resistance wire. 30V voltage is given to the resistance wire. Shortly before the current flowed, oil was dropped on the resistance wire and smoke was obtained as a result of the oil burning. At the wind speed of 6 m/s, separation points on the wing structure were examined in 2° increments, starting from 0° to 18°. In the flow visualization and force analysis, it was seen that the adhesion loss angles were at close values. In addition, the data obtained showed that the pressure differences on the upper and lower surfaces of the wing increased as the angle of attack increased, and the lift coefficient values caused by this pressure difference were found to be compatible with the literature