Robust Flow Control For Radically Enhanced Natural Laminar Flow Wings

Airfoil stagnation point control has the potential to significantly improve the performance of aircraft by producing a radically enhanced natural laminar flow (NLF) low drag wing. By controlling the stagnation point location of an NLF airfoil, the range of low drag lift coefficients can be extended by up to 100%. The objective of this Phase I proposal is to design a hinge-less variable camber full span trailing-edge for airfoil stagnation point control utilizing compliant monolithic structures. The system will provide a significantly enhanced performance envelope for any aircraft able to utilize an NLF wing. In addition to stagnation point control, the system will provide full lateral and lift distribution control of the vehicle while producing a lower radar cross-section, better battle tolerance, and increased maneuvering capability. The new design will provide increased maximum lift in the low drag bucket of the airfoil, thus providing better performance at the design point for the beginning of cruise, resulting in a higher altitude, or more payload to altitude, or more fuel to altitude for longer endurance. Additionally, the drag at low lift coefficients will also be decreased providing higher dash speeds.