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Non-morphing, conventional aircraft wings are designed for a compromise of good performance at a variety of flight conditions. Accordingly, such wings perform sub-optimally when considered at a single flight condition. Morphing trailing edge devices offer an opportunity to change this wing design paradigm by allowing wings to adapt to varying flight conditions. This adaptability weakens the correlation between performance at various flight conditions and increases the robustness of the wing’s performance, providing closer-to-optimal performance at each flight condition. To study the isolated aerodynamic effects of this increased robustness, we performed a number of aerodynamic shape optimizations of a small morphing trailing edge device at a variety of flight conditions on the Common Research Model aircraft configuration. Comparing the performance of the aircraft with a morphing region spanning the aft 10% of the wing and an aircraft without morphing demonstrated a 1.02% fuel burn reduction with the addition of the morphing for a 7,730 nmi mission. We repeated this process with the inclusion of coupled structural deformations and found a fuel burn reduction of 1.72%. This value provides a baseline for the performance improvement potential of this technology, independent of any restrictions or safety factors limiting the use of morphing trailing edge devices for maneuver or gust load alleviation.

Aerostructural design optimization of a continuous morphing trailing edge aircraft for improved mission performance