  Acoustics loads are rocket design constraints which push researches and
engineers to invest efforts in the aeroacoustics phenomena which is present on
launch vehicles. Therefore, an in-house computational fluid dynamics tool is
developed in order to reproduce high-fidelity results of supersonic jet flows
for aeroacoustic analogy applications. The solver is written using the large
eddy simulation formulation that is discretized using a finite-difference
approach and an explicit time integration. Numerical simulations of supersonic
jet flows are very expensive and demand efficient high-performance computing.
Therefore, non-blocking message passage interface protocols and parallel
input/output features are implemented into the code in order to perform
simulations which demand up to one billion degrees of freedom. The present work
evaluates the parallel efficiency of the solver when running on a supercomputer
with a maximum theoretical peak of 127.4 TFLOPS. Speedup curves are generated
using nine different workloads. Moreover, the validation results of a realistic
flow condition are also presented in the current work.
