Experimental investigation of non-slender delta-wing planforms at low reynolds numbers

A proper understanding of vorticity production, reorientation, and annihilation around and in the wake of complex three-dimensional bodies such as unmanned combat air vehicles (UCAVs) would provide critical insight for effective flow-control development in unsteady environments. Force measurement and steady three-dimensional flow visualization of low Reynolds number baseline cases have been carried out on a steady delta wing. Force measurements, which were conducted at angles of attack 10°, 15°, 20°, 25° and 30°, show that coefficient of drag has a tendency to increase with angle of attack, while coefficient of lift reaches its maximum value at 20°. Reconstructed three-dimensional time-averaged flow visualization conducted at angle of attack 10°, 15°, 20°, 25° and 30° shows vortices with larger size and strength are generated and dissipate faster at higher angles of attack. These results compare analogously with similar baseline experimental results at high Reynolds number.