  Wall-modeled large-eddy simulation (WMLES) is utilized to analyze the
experimental aircraft X-59 Quiet SuperSonic Technology (QueSST) developed by
Lockheed Martin at Skunk Works for NASA's Low-Boom Flight Demonstrator project.
The simulations utilize the charLES solver and aim to assess the ability of
WMLES to predict near-field noise levels under cruise conditions, considering
various subgrid-scale (SGS) models and grid resolutions. The results are
compared with previous numerical studies based on the Reynolds-averaged
Navier-Stokes (RANS) equations. Our findings demonstrate that WMLES produces
near-field pressure predictions that are similar to those of RANS simulations
at a comparable computational cost. Some mild discrepancies are observed
between the WMLES and RANS predictions downstream the aircraft. These
differences persist for finest grid refinement considered, suggesting that they
might be attributed to underresolved interactions of shock waves and expansions
waves at the trailing edge.
