Robust Flow Control For Radically Enhanced Natural Laminar Flow Wings

Airfoil stagnation point control will significantly improve the performance of aircraft by producing a radically enhanced natural laminar flow, 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 II proposal is to validate the Phase I design of a radically enhanced NLF airfoil design. The new airfoil design incorporates a compliant structure trailing-edge flap system for stagnation point control. The complaint trailing-edge is used to control stagnation point movement through an automated feedback and control system designed in Phase I. The system will provide a significantly enhanced performance envelope for any aircraft able to utilize an NLF wing. The system will provide full lateral, spanwise lift distribution and gust and maneuver load alleviation control of the vehicle, while producing a lower radar cross-section and better battle tolerance. The system will provide increased maximum lift in the low-drag bucket, providing better performance at the beginning of cruise, resulting in a higher altitude, or more payload to altitude, or more fuel to altitude for longer endurance.