Accurate modeling of high-speed flow-induced noise is of importance in the aerospace industry. However, there is a lack of implementation of modeling algorithms suitable for such high speed noise problems in open-source computational fluid dynamic (CFD) codes. The main aim of this investigation is to model the high-speed flow-induced noise such as jet noise, using the open source tools . Accurate far-field noise computation requires resolution of fine scale turbulence structures in the near field, which act as aeroacoustic sources. Efficient resolution of the fine turbulence structures in the smooth regions of the flow requires the use of accurate high resolution schemes. However, dealing with high speed flows requires an additional consideration of high gradients and discontinuities which can cause numerical oscillations during computation. In this study, a hybrid approach is implemented wherein the flow field is partitioned into two domains corresponding to diffusive and high resolution schemes. Ffowcs William-Hawkings acoustic formulation is implemented as a post processing utility within the computational framework to compute the far-field noise based on the compressible flow data generated. A Mach 0.9 jet is simulated using this setup and the results were validated with experimental data. The aerodynamic and acoustic results are found to be in good agreement with existing experimental data suggesting the adequacy of selected setup for modeling high speed flow induced noise.

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