12 Scopus citations


Supersonic rectangular jet flow and far field noise predictions are made by solving the governing equations using advanced numerical techniques on parallel processors. The computational domain begins at the jet nozzle exit and contains the jet plume and a small region of the acoustic near field. The equations solved for the interior grid points are the full 3D Navier Stoltes equations. The far field boundary points are determined by unsteady, nonlinear characteristic based nonreflecting conditions. To model the jet nozzle exit flow, a set of equations are developed to simulate many features of this flow that have been experimentally observed to influence the jet and its radiated noise. A Kirchhoff method is used to determine the far field noise from information extracted from the finite computational domain. Each set of governing equations is spatially discretized by a sixth order central difference scheme and advanced in time using fourth order Runge-Kutta integration. Spurious high wave number fluctuations are damped by a nonlinear dissipation algorithm that has a minimal effect on the acoustic solution. The code has been efficiently implemented on the CM5 using CMFortran (essentially HPF) and should be easily ported to platforms running HPF (such as the SP2). Numerical results indicate that the algorithm, which contains no model constants (aside from the nozzle exit conditions), is capable of reproducing many experimentally observed rectangular jet flow and noise features.

Original languageEnglish (US)
StatePublished - 1996
Event2nd AIAA/CEAS Aeroacoustics Conference, 1996 - State College, United States
Duration: May 6 1996May 8 1996


Other2nd AIAA/CEAS Aeroacoustics Conference, 1996
Country/TerritoryUnited States
CityState College

All Science Journal Classification (ASJC) codes

  • Electrical and Electronic Engineering
  • Aerospace Engineering


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