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An experimental study was conducted in the NASA Langley Low-Turbulence Pressure Tunnel (LTPT) to evaluate a suction sidewall boundary-layercontrol (BLC) technique used in testing two-dimensional highlift airfoils. Sidewall BLC is required to maintain spanwise twedimensionality of the flow over the airfoil at large angles of attack. A supercritical-type high-lift airfoil, quipped with a double-slotted flap and a leadingedge slat, was used for the study which was conducted at a Mach number of 0.2 and Reynolds numbers based on chord of 9 and 16 million. The sidewall BLC technique, which features distributed suction through porous endplates connected to a venting system, was able to control sidewall boundary-layer separation and maintain two-dimensional flow over the high-lift configuration for both Reynolds numbers tested. Discus-I Mathematician, Low-Turbulence Pressure lunnel Section I' Senior Engineer Scientist

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