In laminar flow investigations, several parameters related to manufacturing quality of the aircraft wind tunnel model have to be taken into account since they can strongly affect the laminar-turbulent transition location. Model shape, steps and gaps, waviness and surface roughness of the model, are key parameters for the quality of laminar flow investigation. Even if this effect is not so amply described in literature where few empirical and inaccurate correlations between the roughness height and the transition position can be found, experimental results have shown that distributed roughness strongly affects the laminar-turbulent transition. This phenomenon can be managed through a very good mechanical design able to avoid possible step and gap coming from the integration of different parts composing the model and taking care, in the manufacturing phase, of the waviness and of the surface refinement, both being challenging tasks. Last, but not least, the number of pressure sensors and their integration in the leading region (necessary to correctly capture the stagnation region) requires special and innovative solutions to avoid laminar flow contamination. Fully in line with JTI-CS2-2017-CfP07-AIR-01-30, the overall objective of the project is to support the development and assessment of natural laminar aircraft integrating innovative aerodynamic control surfaces, and High lift technologies. The EULOSAM II project focuses on the modification and completion of a WT-model that allows analysing of the aerodynamic performance of innovative control surfaces and high-lift devices. Model main size is roughly 2.25 m in span for an area of around 1.2 m^2 with a the Horizontal Tail Plane (HTP) of 0.8 m in span for an area of 0.26 m^2. The WT model has the high aspect ratio of around 11 and a low sweep angle of 20°.

SARAH is concerned with establishing novel holistic, simulation-based approaches to the analysis of aircraft ditching. It is build up from a consortium of experts from OEM industries, experienced suppliers of simulation technologies, established research institutions and representatives of the certification authorities. Results of SARAH are expected to support a performance-based regulation and certification for next generation aircraft and helicopter and to enhance the safe air transport as well as to foster the trustworthiness of aviation services. Aircrafts and helicopters often travel above water and thus have to prove a safe landing under emergency conditions. The specific challenge is to minimize the risk of injury to passengers and to enable safe evacuation. Accordingly, the motion of the aircraft/helicopter along with the forces acting on the structure are studied for controlled water impact during the design phase of an aircraft. Ditching has close links with crash simulation, but also distinctive features. Examples refer to hydrodynamic slamming loads on airborne vehicles and complex hydromechanics (partially at very large forward speeds) as well as the interaction of multi-phase fluid dynamics (involving air, water, and vapor phases) and structure mechanics. Design for ditching involves more than the analysis of loads and subsequent strengthening of the structure. It often requires adjustment campaigns for the handling of the vehicle during approach and the identification of favorable approach/flight-path conditions in line with the pilots flying capabilities to minimize the remaining kinetic energy of the vehicle to be transferred into the water. In conclusion, a pressing need for more advanced studies to support the development of next-generation, generalized simulation-based ditching-analysis practices is acknowledged by all stakeholders. The public interest in safety makes this proposal an ideal candidate for a European research proposal.

U-HARWARD will consider the use of innovative aerodynamic and aeroelastic designs in a multi-fidelity multi-disciplinary optimal design approach to facilitate the development of Ultra-High aspect ratio wings for large transport aircraft. A conceptual design study, building on the current state of the art, will perform trade-off studies to determine the potential gains of different wing configurations and loads alleviation concepts in terms of aerodynamics, weight, noise, fuel-burn and range. Scaled model wind tunnel tests will be used to validate parametric variations in the aerodynamic and acoustic characteristics. Starting from a reference aircraft, the preliminary design of the best candidate configuration will be completed and the estimated gains validated using high fidelity tools and a larger scale aeroelastic test.