<p>A semi-span wing based on the slotted, natural-laminar-flow (SNLF) airfoil concept was experimentally tested in the NASA Ames Unitary Plan Wind Tunnel 11-ft transonic test section to validate the viability of SNLF for commercial transport applications. The model is based on the S207, SNLF airfoil, which was designed in tandem with a transonic, truss-braced wing (TTBW) aircraft as part of a NASA-funded University Leadership Initiative project. The wind-tunnel model itself is a constant-chord, constant-sweep to emphasize the airfoil aerodynamics. Pressure orifices were included in the model and distributed between the fore and aft elements. Total force and moment measurements were collected using a floor balance. Transition locations were measured using IR thermography, facilitated by the model being coated with a high-emissivity black paint with a fine surface finish. The capabilities of the wind tunnel allowed for testing at Reynolds and Mach numbers exceeding those expected for the reference TTBW aircraft, which is notable for ground testing. It was found that the model achieved extensive runs of laminar flow around its design point, validating the concept at flight-relevant conditions. Low-speed testing with the aft element deflected like a Fowler flap showed significant increases in maximum lift compared to the cruise configuration. The goal of the present paper is to expand on this prior work and provide additional data comparisons for the cruise configuration, including sensitivity analyses for both Mach and Reynolds number, evaluation of additional angles of attack, and an assessment of how well the two-dimensional airfoil behavior translates to a three-dimensional wing. Altogether, the data confirm the viability of SNLF for commercial transport applications by showing very long runs of laminar flow at flight-relevant conditions.</p>