Modification of static-wing tip vortex via a slender half-delta wing

作者：Lee T^*; Pereira J

来源：Journal of Fluids and Structures, 2013, 43: 1-14.

DOI：10.1016/j.jfluidstructs.2013.08.004

• Experimental fluid dynamics
• Wingtip vortex and its control
• Lift-induced drag computation
• Vortex flow

The modification of the tip vortex generated by a rectangular NACA 0012 wing via a tip-mounted slender half-delta wing (HDW) was attempted experimentally at Re = 2.81 x 10(5). In addition to the increase in lift with increasing HDW deflection, compared to the baseline wing, the roll-up process of the tip vortex was also found to be significantly modified, as a result of the breakdown of the HDW vortex. The addition of the HDW also caused an increased total drag. Fortunately, the lift-induced drag was found to be reduced compared to its baseline counterpart for 0 degrees and 5 degrees HDW deflections. The change in the lift-induced drag also translates into a virtually unchanged profile drag, regardless of HDW deflection. In short, the largest lift-induced drag reduction achieved by the zero-deflection HDW resulted in an improved lift-to-drag ratio, at high angle-of-attack range, compared to the baseline wing.

• 出版日期2013-11