Experimental studies of a 70-degree delta wing with vortex flaps

Force, surface pressure, and flowfield measurements were made on a 0.5-m root chord, 70-deg delta wing model with leading-edge vortex flaps at the National Aerospace Laboratory, Japan. The main objective of the experiment is to investigate the effect of the wing sweepback angle upon the vortex flap performance. Improvements in the lift/drag ratio were observed in a 70-deg delta wing by deflecting the tapered vortex flaps.