The three-dimensional flowfields over finite span wings and in their wake were explored experimentally in a low-speed, closed-return, open test section water tunnel using flow visualization. The wings had a NACA 0015 profile and were suspended in the tunnel allowing for the wings to generate tip vortices on either end. Wings with aspect ratios of 2 and 4 were tested at an angle of attack of 22 degrees and chord Reynolds number of 600 and 1000 to understand how the flowfield is affected with alteration of the aspect ratio and/or Reynolds number. Thew effect of sweep was also explored.
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