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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 , 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