Trailing-edge data for boundary-layer/near-wake thickness parameters are given for airfoils and flat plates. Reynolds number effects are examined as a function of model size, velocity and boundary-layer tripping. Reference comparisons are made with boundary-layer calculations using potential-flow modeling and a finitedifference method for laminar and turbulent boundary layers. Open wind-tunnel corrections to angle of attack and camber are incorporated into the potential-flow modeling. It was found that the open tunnel flow turbulence affects early boundary-layer transition for the higher velocities. The theory still "brackets" the data allowing some assessment of boundary-laye r transition behavior.