Flow physics and control of 3-D separation over swept and tapered wings at a low Reynolds number

An experimental investigation of flow control by steady blowing over swept and tapered wings was performed in a series of water tunnel experiments with a mean-chord Reynolds number of 600. Two NACA 0015 wings were explored each with a semi-aspect ratio of 2 and taper ratio of 0.269. One wing had an unswept leading edge and a 30 degree swept forward trailing edge and the other wing had a 30 degree swept back leading edge and an unswept trailing edge. The effect of the spanwise location of steady blowing was explored for each wing, where a single jet with a blowing ratio of 1 was placed at either 25%, 50%, or 75% of the span. SPIV volumetric flowfield measurements were collected for each case at an angle of attack of 18 and 22 degrees. The effect of spanwise location of the jet on the formation of the large-scale flow structures is presented.