p Pressure

from computational fluid dynamics solutions are gathered from nineteen participants rep-resenting three countries for the two required cases, an axisymmetric body and simple delta wing body. Structured multiblock, unstructured mixed-element, unstructured tetra-hedral, overset, and Cartesian cut-cell methods are used by the participants. Participants provided signatures computed on participant generated and solution adapted grids. Sig-natures are also provided for a series of uniformly refined workshop provided grids. These submissions are propagated to the ground and noise measures are computed. This allows the grid convergence of a noise measure and a validation metric (difference norm between computed and wind tunnel measured near-field signatures) to be studied for the first time. A statistical analysis is also presented for these measures. An optional configuration in-cludes fuselage, wing, tail, flow-through nacelles, and blade sting. This full configuration exhibits more variation in eleven submissions than the sixty submissions provided for each required case. Recommendations are provided for potential improvements to the analysis methods and a possible subsequent workshop. Nomenclature b Wing span dp/pinf Freestream pressure difference normalized by freestream h Characteristic spacing of the grid H Distance below the model K Coverage factor L Model reference lengt