A slotted, natural-laminar-flow (SNLF) airfoil, the S414, was designed for rotorcraft applications with the primary objectives of high maximum lift and low profile drag in conjunction with satisfying a thickness constraint. Previous measurements taken in the Pennsylvania State University Low-Speed, Low-Turbulence Wind Tunnel, along with theoretical analyses using MSES and OVERFLOW, demonstrate that the design objectives have been met. The overall aim of the effort reported herein is to advance the SNLF concept toward practical application. To accomplish this goal, a better understanding of the aerodynamic interaction between the fore and aft elements is sought by exploring different positions of the fore and aft elements relative to one another. The results confirm the potential of the SNLF airfoil concept and provide a better understanding of the use of the aft element as a control surface. While it is clear that the aft element could be “scheduled” to operate as a flap and/or aileron, incorporating a control surface into the aft element promises to be more effective and much less complicated. Comparisons of computed aerodynamic characteristics with those obtained experimentally show good agreement.