02.2 - Experimental Aerodynamics
EFFECTS OF REYNOLDS NUMBER ON THE ONSET OF LEADING EDGE VORTEX SEPARATION ABOVE BLUNT-EDGE DELTA WING VFE-2 CONFIGURATIONS
M. Said¹, S. Mat¹; ¹AeroLab, Universiti Teknologi Malaysia, Malaysia
This paper discusses the effects of Reynolds number on the passage of leading-edge vortex separation onset above blunt-edge delta wing VFE-2 configurations. Two type of leading edge; medium and large radius wing, were tested in UTM wind tunnel. The correlation of the leading-edge pressure coefficients with the onset and progression of leading-edge separation are discussed. The tests in this study were performed at speeds correspond to Reynolds numbers of 1.0?106, 2.0?106and 3.0?106 and based on the mean aerodynamic chord. The experiments showed that an increase in Reynolds number can delay the formation of the primary vortex towards the aft portions of the wing.