TY - CONF
T1 - Numerical predictions of high speed jet noise
AU - Morris, Philip J.
AU - Wang, Qunzhen
AU - Long, Lyle N.
AU - Lockard, David P.
N1 - Funding Information:
This work is supported by NASA Langley Re- search Center under task order NAS1-20102. The technical monitor is Mr. R.A. Golub. The program is administered by Lockheed Martin Aeronautical Systems Corporation. The project manager is Dr. N. N. Reddy. The authors acknowledge the help of Dr. Andrew T. Thies who provided the RANS mean
Publisher Copyright:
© 1997, American Institute of Aeronautics and Astronautics, Inc.
PY - 1997
Y1 - 1997
N2 - A parallel three-dimensional computational aeroacoustics method, based on large eddy simulation and a split between the mean flow and perturbations, has been developed to predict the unsteady characteristics of supersonic jet flows and their radiated noise. The instantaneous quantities are decomposed into a time-independent mean component, a large-scale perturbation, and a small-scale perturbation. Only the large-scale fluctuations are resolved directly while the mean quantities are obtained from a traditional Reynolds averaged method. The effects of the small-scale fluctuations are parameterized using a subgrid scale model. In order to reduce the wall-clock time for the simulations, the three-dimensional code has been parallelized using a domain decomposition strategy and Message Passing Interface (MPI) routines are used to facilitate exchange of data between different processors. Results for both the flow and acoustic fields of a circular jet simulation at a nozzle exit Mach number of 2.1 are presented and comparisons with several experimental measurements are made.
AB - A parallel three-dimensional computational aeroacoustics method, based on large eddy simulation and a split between the mean flow and perturbations, has been developed to predict the unsteady characteristics of supersonic jet flows and their radiated noise. The instantaneous quantities are decomposed into a time-independent mean component, a large-scale perturbation, and a small-scale perturbation. Only the large-scale fluctuations are resolved directly while the mean quantities are obtained from a traditional Reynolds averaged method. The effects of the small-scale fluctuations are parameterized using a subgrid scale model. In order to reduce the wall-clock time for the simulations, the three-dimensional code has been parallelized using a domain decomposition strategy and Message Passing Interface (MPI) routines are used to facilitate exchange of data between different processors. Results for both the flow and acoustic fields of a circular jet simulation at a nozzle exit Mach number of 2.1 are presented and comparisons with several experimental measurements are made.
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U2 - 10.2514/6.1997-1598
DO - 10.2514/6.1997-1598
M3 - Paper
AN - SCOPUS:84977178293
T2 - 3rd AIAA/CEAS Aeroacoustics Conference, 1997
Y2 - 12 May 1997 through 14 May 1997
ER -