Flow-field measurements were obtained in the wake of a full-span Hybrid Wing Body model featuring steady blowing through internally blown flaps. The test was performed at the NASA Langley 14×22 Foot Subsonic Tunnel at low speeds. Off-body measurements were obtained with a 7-hole probe rake survey system. Three model configurations were investigated. At 0° angle of attack the surveys were completed with 0° and 60° flap deflections. At 10° angle of attack the wake surveys were completed with a slat and a 60° flap deflection. The 7-hole probe results further quantified two known swirling regions (downstream of the outboard flap edge and the inboard/outboard flap juncture) for the 60° flap cases with blowing at both angles of attack. Flow-field results and the general trends are very similar for the two blowing cases at nozzle pressure ratios of 1.37 and 1.56. High downwash velocities correlated with the enhanced lift for the 60° flap cases with blowing. Jet-induced effects are the largest at the most inboard station for all (three) velocity components due in part to the larger inboard slot height. The experimental data are being used for the validation of computational tools for high-lift wings with integrated powered-lift technologies.