Numerical simulations of compressible, turbulent jets using the Shear Stress Transport (SST) κ-ω model have been carried out for baseline nozzle and chevron nozzles with 6 lobes for three different penetration angles. The predicted flow performance and far-field noise production were compared with the experimental data available in the literature. The 3D calculations have been done on a hexahedral mesh with 1.1 million cells in a 30° pie sector for the baseline nozzle. A hybrid mesh of 1.5 million cells were used for chevron simulation in a view to keep the wall y+ less than 10. Both cold and hot jets have been simulated. The jet exit velocity simulated for both the cases are approximately 300 m/s. Overall sound pressure levels at far-field observer locations have been calculated using FfowcsWilliams-Hawkings equation. Numerical prediction of stagnation pressure, stagnation temperature, turbulent kinetic energy and 90° observer spectral trends were compared with experimental data. The potential core length is predicted well, but the predicted centerline velocity decay is faster than the measured value. The URANS calculations are able to predict the absolute values for the overall SPL, but the predicted spectral trends are very poor. The calculations predict the flow performance characteristics like stagnation pressure, temperature and peak values of turbulent kinetic energy reasonably well for both cold and hot jets. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc.