Multi-fidelity approach for sonic boom annoyance

The following abstract aims at summarizing the multi-fidelity approach developed in the framework of the H2020 MORE&LESS project for the evaluation of sonic boom phenomena from a physical and psychoacoustic point of views for different aircraft configurations. Starting from the conceptual design phase, new analytical formulations shall be developed and validated to accurately define sonic boom without the necessity of having high time-consuming simulations. Then, once a 3D CAD model is available, numerical higher-fidelity simulations can be carried out. This step consists of both the near-field CFD and the use of a propagation code to propagate the shocks from the aircraft altitude to the ground. The H2020 MORE&LESS offers the opportunity to validate formulations and numerical results thanks to open-field test campaigns with small-scale aircraft models. Finally, having all information regarding the ground signature, a psychoacoustics code can be employed to define the annoyance caused by sonic boom comparing different noise metrics. Throughout the paper, the preliminary results available for a Mach 5 waverider configuration are reported.