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Carried out in the TsAGI T-107 subsonic wind tunnel (test section diameter dw.t. = 2.7 m.) has been the experimental investigation of subsonic flow -9.4·106) about a large-scale half-model (span 1.67 m, chord 0.73 m) of a swept untapered wing (χ = 35°, η = 1, c̄ = 9.8%) equipped with a local boundary-layer suction system . Based on a measured pressure distributions, angles of attack were selected (α = -2° and -4°) to be rational from the standpoint of cross-flow disturbance's development. The extent of the laminar flow zone was determined through various methods. Based on the losses of the total pressure measured in the wake behind the mid-section of the swept portion of the model, the decrease in the section drag was estimated due to local boundary-layer suction. Several laws and suction rates as well as the chordwise extents of the suction region were tested with the aim of obtaining a maximum decrease in the section drag of the swept wing.