A complementary experimental and numerical investigation was performed to study the 3-D flow structures and interactions of finite-span synthetic jets in a cross-flow at a chord-based Reynolds number range from 50,000 to 400,000 and angles of attack between 0 0 to 20 0 . A range of momentum coefficients was considered corresponding to six different blowing ratios in the range of 0.2 to 1.2 with an increment of 0.2 (where, the blowing ratio is defined based on the averaged outstroke jet velocity to the free-stream velocity). Experiments were conducted on two finite wings (unswept and 30 0 swept-back configurations) with a cross-sectional profile of NACA 4421, where both 2-D and stereoscopic PIV data were collected at various spanwise locations along the wing. In complement to the experiments, 3-D numerical simulations were performed, where the numerical setup not only matched the physical parameters (e.g., free-stream, blowing ratio, etc.) but also the physical dimensions (e.g., orientation and location of jet, flow control cavity including slot and chamber, etc.). Note that the numerical simulations only address one topic, which is the interaction of a single synthetic jet with a cross-flow over the unswept wing configuration, whereas the experiments included three sets of data: (1) a single finite span synthetic jet interacting with a finite unswept wing, (2) a single finite span synthetic jet interacting with a finite sweptback wing, and (3) multiple finite span synthetic jets interacting with a finite unswept wing.I.