Browsing by Author "Villena Munoz, Cristina"

Now showing 1 - 4 of 4
  • Thumbnail Image
    ItemOpen Access
    Conceptual design of a next generation supersonic airliner for low noise and emissions
    (AIAA, 2023-01-19) Villena Munoz, Cristina; Bonavolontà, Giordana; Lawson, Craig;; Riaz, Atif
    The development of an innovative, medium-range supersonic airliner to meet low drag, low emissions and LTO noise requirements is presented in this paper, including a multi-disciplinary design framework targeting firstly to meet at least the current noise regulations for subsonic aircraft during take-off and landing and secondly to reduce the emission levels. The aircraft is designed to fly 4000 nm at Mach 2.2, carrying 100 passengers. The work contributes to the EU SENECA ((LTO) noiSe and EmissioNs of supErsoniC Aircraft) project, which aims to design different SST (SuperSonic Transport) aircraft platforms to investigate the emissions, the noise and the global environmental impact of supersonic aviation. Results from SENECA can support ICAO in the process of creating future certification requirements as well as form legislation guidelines specifically for the future supersonic commercial aircraft. The technical work includes the assessment of different aircraft-engine configurations, in terms of engine number and positions, on typical flight missions. This enables the evaluation of the baseline layouts that represent the best compromise among payload-range capability, aerodynamic performance, weight and noise. A multi-disciplinary airframe-engine integrated design is carried out in order to pursue a comparative analysis focusing on take-off noise for the different aircraft-engine combination platforms. Lastly, the investigation of the potential use of variable noise reduction systems (VNRS), such as a FADEC controlled thrust reduction during take-off, called Programmed Lapse Rate (PLR) is carried out to study their impact in the mitigation of the resultant noise in the airport environment.
  • Thumbnail Image
    ItemOpen Access
    Conceptual design of supersonic aircraft to investigate environmental impact
    (AIAA, 2024-01-04) Villena Munoz, Cristina; Lawson, Craig;; Riaz, Atif; Jaron, Robert
    The SENECA ((LTO) noiSe and EmissioNs of supErsoniC Aircraft) project, funded under the EU Horizon 2020 framework, is dedicated to the exploration of future designs for supersonic business jets and supersonic commercial airliners, placing significant emphasis on minimising landing and take-off noise and mitigating emissions. The research outcomes are intended to inform discussions at ICAO level, providing scientific support to enhance the European perspective on regulatory requirements for novel supersonic aircraft. The overall aim of the research is the development of four different supersonic transport aircraft platforms, comprising both airframes and engines design. These aircraft configurations range from supersonic business jets, designed for cruise Mach numbers of 1.4 and 1.6, to large airliners capable of accommodating 100 passengers, with cruise Mach numbers of 1.8 and 2.2. In pursuit of the next generation of environmentally sustainable supersonic civil aircraft, the research employs a multi-disciplinary design optimisation strategy. This strategy primarily focuses on meeting the current noise regulations for subsonic aircraft during landing and take-off and secondly on reducing emissions levels. This paper details the conceptual development of the platforms specifications for the four supersonic aircraft designed within SENECA project. These specifications include geometrical and configuration data, performance characteristics, as well as mission trajectories and profiles.
  • Thumbnail Image
    ItemOpen Access
    Single- and two-stage fan designs for a supersonic airliner with focus on certification noise reduction
    (AIAA, 2025-01-06) Graebert, Matti; Jaron, Robert; Villena Munoz, Cristina; Plohr, Martin; Moreau, Antoine
    A comprehensive analytical approach is taken to compare the aerodynamic performance as well as the landing and take-off noise of a single and a two-stage fan at pre-design level. The fans were designed for the engines of a supersonic airliner with the goal of minimizing noise certification levels. The prediction of aerodynamic performance is performed for on- and off-design points using analytical and semi-empirical models, the noise for landing and take-off operations is calculated using analytical approaches in modelling noise sources and propagation to the certification points. Certification metrics are also calculated and used in this comparison. This process is run for both fan designs on a baseline take-off trajectory in accordance with current regulations, as well as an optimized trajectory exploiting potential regulation changes for supersonic aircraft. With this study, the authors are able to demonstrate that a two-stage fan design produces significantly lower noise levels. In configurations and on trajectories on which fan noise is dominant, significantly lower certification levels could be achieved.
  • Thumbnail Image
    ItemOpen Access
    Toward quieter and more efficient supersonic flight: multi-objective optimization of a Bell-Shaped Lift Distribution wing SSBJ
    (AIAA, 2024-01-04) Bonavolontà, Giordana; Manoj, Anirudh; Villena Munoz, Cristina; Tajesh Chilukuri, Sai; Lawson, Craig;; Riaz, Atif
    The optimization for low drag and boom of a new promising supersonic aircraft concept is presented in this paper. The Bell-Shaped Lift Distribution wing concept by Prandtl has been explored by the authors to design and optimize a supersonic business jet. This historical concept, known to be a theoretical solution for minimum induced drag wing, has been applied to redesign the SENECA E-19 Supersonic business jet wing. After having demonstrated that a bell span loading operates as intended in the supersonic regime, the configuration so designed has been optimized for low drag and boom by varying fuselage and tail design parameters. In addition, different combinations of engine positions have been also investigated within the optimization loop. The NSGA-II genetic algorithm has been chosen to carry out the multi- objective optimization. Low-to-medium fidelity numerical methods have been implemented to obtain the aerodynamic solution, while in-house multi-level of fidelity tool based on well-known methods has been used to perform sonic boom assessment. Take-off airframe noise assessment has been also performed on the final configuration resulting from optimization. The final configuration shows 6 % increase in aerodynamic efficiency and 7 % in boom with respect to the baseline.