A large-chord, swept, supercritical, laminar-flow-control (LFC) airfoil was designed and constructed and is currently undergoing tests in the Langley 8 ft Transonic Pressure Tunnel. The experiment was directed toward evaluating the compatibility of LFC and supercritical airfoils, validating prediction techniques, and generating a data base for future transport airfoil design as part of NASA's ongoing research program to significantly reduce drag and increase aircraft efficiency. Unique features of the airfoil included a high design Mach number with shock free flow and boundary layer control by suction. Special requirements for the experiment included modifications to the wind tunnel to achieve the necessary flow quality and contouring of the test section walls to simulate free air flow about a swept model at transonic speeds. Design of the airfoil with a slotted suction surface, the suction system, and modifications to the tunnel to meet test requirements are discussed. Harris, Charles D. and Harvey, William D. and Brooks, Cuyler W., Jr. Langley Research Center BOUNDARY LAYER CONTROL; LAMINAR BOUNDARY LAYER; LAMINAR FLOW; SUPERCRITICAL AIRFOILS; SWEPT WINGS; AIRCRAFT DESIGN; DRAG REDUCTION; FREE FLOW; GENERAL OVERVIEWS; PREDICTION ANALYSIS TECHNIQUES; SUCTION; TRANSONIC SPEED; WIND TUNNEL TESTS; WIND TUNNEL WALLS; WING SLOTS...