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Item type:Publication, Access status: without files , Sonic boom velocity and altitude sensitivity analysis of a hypersonic aircraft conceptDuring the last decades there has been a renewed interest in the development of a new generation of supersonic aircraft for civil purposes with limited implications to the environment. However, the noise generated by supersonic aircraft during supersonic flight, commonly referred to as "sonic boom", still creates annoyance to community on the ground that prohibits supersonic overland flight. To prepare for the advent of a new generation of supersonic aircraft and to define new regulations for them, an increasing number of sonic boom studies is being published. This paper presents numerical simulations of the sonic boom of a hypersonic (Mach 5) aircraft concept during the full flight envelope, including a sensitivity analysis of the two parameters velocity and altitude. The extensive simulations characterize the sonic boom distribution on ground, which is usually referred to as "sonic boom carpet", caused by the aircraft for different speeds between Mach 1.2 and Mach 5.0, and for two altitudes of 11.3 km and 28.0 km above sea level. Different loudness metrics were calculated for the different flight conditions, including PLdB, ISBAP and SEL related metrics. The simulation approach is divided into two main regions. This approach is well understood and was validated during the three NASA Sonic Boom Prediction Workshop held between 2014 and 2021: The dual approach consists of (1) a near-field domain computed with Computational Fluid Dynamics (CFD) using a hybrid mesh and a Fluent solver based on ROE-FDS numerical scheme, and (2) a far-field propagation algorithm based on ray tracing and a nonlinear, one-dimensional shock wave propagation algorithm (Augmented Burgers Equation). The results highlight the differences in sonic boom behavior and loudness metrics due to Mach number and altitude variation. The propagation results are compared with the ones given by NASA's PCBoom software.Publicationtype: Conference Paper164 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: with files , Evaluation of sonic boom shock wave generation with CFD methods(Multidisciplinary Digital Publishing Institute (MDPI), 2024-06-19); ; ; ; Over the past two decades, there has been a renewed interest in the development of a new generation of supersonic aircraft for civil purposes that could potentially succeed Concorde. However, the noise annoyance is still considered one of the hampering factors to meet public consensus. This paper aims at revealing the potential of numerical simulations to predict sonic boom signature in Near Field at early design stages. In particular, the paper further demonstrates the applicability of the numerical approach proposed by NASA and other partners during the Sonic Boom Prediction Workshops held between 2014 and 2021, to compute the pressure signature of aircraft in the zone close to it. The results highlight the suitability of the approach (1) to capture the impact of aircraft flight condition variations on the sonic boom signature, (2) to enable the characterization of novel aircraft layout, including Mach 5 waverider configuration, (3) to provide near-field shock wave noise predictions that can be used to evaluate shock propagation, on-ground signature analyses, and annoyance assessment.Publicationtype: Journal Article23 253 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: without files , ESATTO : the holistic framework to support the design of sustainable supersonic aviation(International Council of the Aeronautical Sciences, 2024); ; 24 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: without files , Comparison between simplified approach and CFD & propagation tool for sonic boom estimation(American Institute of Aeronautics and Astronautics (AIAA), 2023-06); ; ; The following paper compares results obtained through a simplifying methodology that can be used at the conceptual design phase with results obtained through CFD and then propagation code for ground signature. The application of state-of-the-art models for future supersonic aircraft is discussed within the paper and solutions to overcome these limitations will be presented. Validation using CFD techniques and propagation tools is necessary to accurately define which design and flight condition characteristics most affect noise generation and propagation, as well as to integrate and improve existing methods in the literature with new formulations to estimate sonic boom at an early stage of design. The following workflow was validated for an aircraft with a Concorde-like configuration within the EU-funded MORE&LESS project.Publicationtype: Conference Paper27 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: without files , H2020 stratofly project: from europe to australia in less than 3 hoursAs eluded in previous studies, with special reference to those carried out in the European framework, some innovative high-speed aircraft configurations have now the potential to assure an economically viable high-speed aircraft fleet. They make use of unexploited flight routes in the stratosphere, offering a solution to the presently congested flight paths while ensuring a minimum environmental impact in terms of emitted noise and green-house gases, particularly during stratospheric cruise. However, only a dedicated multi-disciplinary integrated design approach could realize this, by considering airframe architectures embedding the propulsion systems as well as meticulously integrating crucial subsystems. In this context, starting from an in-depth investigation of the current status of the activities, the STRATOFLY project has been funded by the European Commission, under the framework of Horizon 2020 plan, with the aim of assessing the potential of this type of high-speed transport vehicle to reach Technology Readiness Level (TRL) 6 by 2035, with respect to key technological, societal and economical aspects. This paper aims at summarizing the main results achieved so far to solve the main issues related to thermal and structural integrity, low-emissions combined propulsion cycles, subsystems design and integration, including smart energy management, environmental aspects impacting climate change, noise emissions and social acceptance, and economic viability accounting for safety and human factors.Publicationtype: Conference Paper77