Leading edge delta vortex generator for boundary layer control on a NACA 63-218 modified wing

Systematical experimental program was carried out to test the effectiveness of the delta vortex generator as a boundary layer control device using realistical wing model at moderate Reyolds number. This paper studies effectiveness of the delta vortex generators on a NACA63-218 modified two dimensional wing using a low-speed, low turbulence, return type wind tunnel where air speed can be varied from 1-50m/s with a turbulence level of less than 01.%. Test with delta vortex generators at leading edge of an airfoil shows significant effect with the favorably stall and drag characteristics reconfirming effectiveness of the delta vortex generator as a boundary layer control device