# Design and Optimization of a Compliant Morphing Trailing Edge for High-Lift Generation
## 8 Conclusions and Further Steps  
This study focused on the research and optimization of a compliant trailing edge architecture that generates high lift in cooperation with a droop nose system and a flow control strategy. The device, in particular its smooth geometry, was conceived to adequately support take-off and landing phases and, at the same time, avoid any disturbance in clean configuration and in this way preserving cruise performance. The system was conceived for a strut-braced wing of a next-generation hybrid electric regional aircraft, driving the following stage of the advanced design of the same device. The authors implemented a multi-step design approach on the basis of the experience gained on previous architectures  
Figure 18: Lift coefficient vs. AoA vs. configuration vs. reference: Eulerian curves for the target morphed shape (black \(\square\)) and configuration 3 (black \(\square\)); RANS curves of the target morphed shape (black o) and for configurations 1–5 (colored o); most severe requirement (C\({}_{\text{L,MAX}}\) in landing, red). already considered for the project. The layout was optimized with the aim of approaching a prescribed morphed shape conceived to achieve the desired maximum lift coefficient level. As a result, a structure with an effective load-bearing capability was determined, with benefits in terms of stress level and force required by the actuation system. All these aspects favorably contribute to the requirements that form the basis of this study:  
* Enhanced aerodynamic performance in cruise due to the absence of any geometrical asperities and flap track fairings;
* Reduced weight, as both the trailing edge structure and the actuation are lighter;
* Abatement of maintenance costs and extended operational life due to greater ease of inspection and a well-distributed load;
* Smaller take-off and landing distances, assured by an adequate maximum lift coefficient and by the reduction in weight. The above achievements and the finalization of the advanced design of the system pave the way for the next steps of the project:  
* Definition of a dedicated test campaign for testing on the ground. The test plan will include functional validation under the most severe load conditions, static tests to verify the capability of the structure of absorbing loads without any damage, and dynamic characterization to exclude any potential coupling problem with the wing structure;
* Manufacturing of a full-sized prototype of the trailing edge segment and preparation of the test setup and test rig;
* Execution of the ground tests and assessment of the results. The previously mentioned activities are in line with the target of the project of maturing this concept up to TRL 5. Conceptualization, S.A., P.C., L.P. and B.B. ; methodology, S.A. and I.D. ; formal analysis, M.C.N., B.G., L.P., B.B. and J.D. ; validation, L.P., S.S., J.D. and B.B. ; investigation, F.A.D., P.C. and M.C.N. ; data curation, F.A.D., B.G. and M.C.N. ; writing--original draft preparation, S.A., P.C. and L.P.; writing--review and editing, S.A., P.C., S.S. and J.D. ; supervision, A.C., G.M.C., J.D., S.S. and S.A.; project administration, P.C., S.S. and J.D. All authors have read and agreed to the published version of the manuscript. This research was funded by Clean Aviation Joint Undertaking under the European Union's Horizon Europe research and innovation program under grant agreement ID 101102010 (HERWINGT Project; [[https://doi.org/10.3030/101102010](https://doi.org/10.3030/101102010)]([https://doi.org/10.3030/101102010](https://doi.org/10.3030/101102010))). Not applicable. Data availability Statement: Data are contained within the article. This study is part of the Hybrid Electric Regional Wing Integration Novel Green Technologies project (HERWINGT).