Improvement on Open Source CFD Methodology To Evaluate Near-Field Sonic Boom

The correct evaluation of the near-field pressure signature of an aircraft is crucial to correctly predict the aircraft noise on the ground. Using a computational fluid dynamic methodology, the differences on the numerical mesh grid, or the use of appropriate numerical schemes, can lead to different solutions. In this work, an effort is made to investigate the effect on noise prediction of various numerical approaches available in an open source solver, applied to reference aircraft model. Particular attention was paid on the construction of the numerical grid, that is hybrid: part of the mesh follows the structured approach, while the other part follows the unstructured one. In this case, the transition of the pressure signal between the two different grids is critical for the correct noise simulation.