GUDGET answers the CfP JTI-CS2-2018-CfP08-AIR-01-38 and aims at providing an innovative experimental set-up for the investigation of gust loads, to be installed in the transonic facility ONERA S3Ch. The proposal GUDGET will design, manufacture, calibrate, verify and finally install in the ONERA S3Ch WT an enhanced gust generator system and an aeroelastic half-model connected to the WT side wall, with the purpose to support the TM in the execution of a WT test campaign and gather information on the aeroelastic behaviour of the model under high amplitude gust conditions, with the acquisition of a relevant database which will allow to assess the numerical capabilities to predict gust loads. The WT test campaign is outside the scope of the GUDGET project. At this aim, the consortium GUDGET has to perform the design of the experimental setup: design and manufacture the WT model according to technical requirements provided by the TM. Special care will be dedicated to the dynamic characteristics of the final model and that a specific interface with the WT will be implemented. In parallel, the consortium will perform a preliminary trade-off analysis to find the best configuration of the GG to comply with requirements dictated in the topic, by considering innovative configurations of tilting airfoils moved by mechanical actuators as well as blowing slots fed by fluidic actuators or a combination of both. The best solution over a number of candidates will be chosen as the one to be designed in detail and then manufactured, calibrated/ verified and eventually installed in the WT. The GUDGET consortium has been setup by joining well recognized and very experienced companies and universities: IBK and POLIMI with a strong experience in the design, manufacturing and operating of WT models; DREAM for supporting CFD and numerical analysis; AVDES for the manufacturing activities and CTEC for the design and implementation of actuation devices.

HERA will identify and trade-off the concept of a regional aircraft, its key architectures, develop required aircraft-level technologies and integrate the required enablers in order to meet the -50% technology-based GHG emission set in SRIA for a Hybrid-Electric Regional Aircraft. The HERA aircraft, having a size of approximately of 50-100 seats, will operate in the regional and short-range air mobility by mid-2030 on typical distances of less than 500 km (inter-urban regional connections). The aircraft will be ready for future inter-modal and multi-modal mobility frameworks for sustainability. The HERA aircraft will include hybrid-electric propulsion based on batteries or fuel cells as energy sources supported by SAF or hydrogen burning for the thermal source, to reach up to 90% lower emissions while being fully compliant with ICAO noise rules. The HERA aircraft will be ready for entry into service by mid-2030, pursuing to the new certification rules, able to interact with new ground infrastructure, supporting new energy sources. This will make HERA aircraft ready for actual revenue service offering to operators and passengers sustainable, safe and fast connectivity mean at low GHG emissions HERA will quantitatively trade innovative aircraft architectures and configurations required to integrate several disruptive enabling technologies including high voltage MW scale electrical distribution, thermal management, new wing and fuselage as well as the new hybrid-electric propulsion and related new energy storage at low GHG. To support this unprecedented integration challenge, HERA will develop suitable processes, tools and simulation models supporting the new interactions, workshare in the value chain and interfaces among systems and components. HERA will also elaborate on the future demonstration strategy of a hybrid–electric regional aircraft in Phase 2 of Clean Aviation to support the high TRL demonstration required for an early impact for HERA solutions.

According to the requirements of the topic JTI-CS2-2018-CFP08-REG-03-01, the proposal ESTRO will produce experimental and numerical data in flow speed and in “cruise conditions” to validate the relevant aerodynamic performance of the Regional 90 sit turboprop A/C wing including laminar flow extension measurements and wing span load distribution. In particular, the tests in wind tunnel conditions will be performed at some Reynolds numbers, whose higher value is expected to be around 7-8 millions, and at low and medium Mach numbers. Accurate pressure distributions, infrared flow images, wing deformation, wall balance and load control and alleviation measurements are expected. The data will be the result of an experimental test campaign performed in a Laminar Wind tunnel with the main objective to evaluate the laminar flow robustness, the aerodynamic performances and load control effectiveness of a turboprop A/C wing at medium/low speeds (Mach numbers up to 0.38) and wind tunnel Reynolds number around 7-8 million. Numerical simulations aim to first assess the wind tunnel experimental results and then to extrapolate the data to flight conditions. In addition, the effects of the propeller on the wing laminar flow extension will be evaluated through 3D boundary layer computations coupled to linear stability analyses based on ray theory.

MYTHOS proposes to develop a demonstrated innovative and disruptive design methodology for future short/medium range civil engines capable of using a wide range of liquid and gaseous fuels including SAFs and, ultimately, pure hydrogen, thus aiming at fulfilling the objective of decarbonize civil aviation as fore-seen by the ACARE SRIA short, mid and long-term Goals by 2050. To achieve these, the MYTHOS consor-tium develops and adopts a multidisciplinary multi-fidelity modelling approach for the characterization of the relevant engine components deploying the full power of the method of machine learning. The latter will lead through hidden-physics discovery to advance data-driven reduced models which will be embedded in a holistic tool for the prediction of the environmental footprint of the civil aviation of all speeds. A unique aspect of the project is the high-fidelity experimental validation of the numerical approaches. MYTHOS consortium through this approach will contribute to reduce time-to-market for engines designed and engi-neered to burn various types of environmentally friendly fuels, such as SAF, in the short and medium term, and hydrogen, in the long term. The proposed work responds to the needs and objectives of the HORIZON-CL5-2022-D5-01-12: Towards a silent and ultra-low local air pollution aircrafts Call as described in detail below.

The main aim of the CA3ViAR project is the design of an Open-Test-Case Fan geometry that will develop instability mechanisms which are representative for UHBR fans of civil aircrafts and perform a comprehensive experimental investigation to measure aerodynamic, aeroelastic and aero-acoustic performance in a wide range of operational conditions. Experimental tests will be performed in the Propulsion-Test-Facility (PTF) of the Institut für Flugantriebe und Strömungsmachinen (IFAS) of Braunschweig, Germany. The proposal CA3ViAR will target several objectives. Initially a literature review of the main issues affecting composite UHBR engine fans will be performed by the Technische Universität Braunschweig (TUBS). The design of the Low-Transonic Fan (LTF) will be led by TUBS with support from DREAM (an Italian SME) in terms of aerodynamic shaping as well as from Leibniz Universität Hannover (LUH) and IBK in terms of aeroelasticity and aeroacoustics. The LTF test article, to be mechanically designed by IBK, will be conceived in a way to experience aerodynamic and aeroelastic instabilities in an expected way during wind-tunnel operations. Manufacturing-related activities will be performed by ADC, a well-recognized manufacturer specialized in aerospace parts and components made of composite and metallic materials, while requirements for the test article integration will be provided by TUBS, responsible of WT instrumentation and operations. The execution of the experimental tests aimed at measuring fan instabilities (e.g. stall, flutter, etc.) will be performed by TUBS with support from LUH. The last technical phase of the project will be the calibration and the eventual validation of aerodynamic, aeroelastic and aeroacoustic models according to WT test data acquired in the PTF. This last technical phase will be led by LUH, with a strong support from all the other partners.