Direct simulation of a Mach 1.92 jet and its sound field

J. B. Freund, S. K. Lele, P. Moin

Research output: Contribution to conferencePaper

Abstract

A perfectly expanded turbulent Mach 1.92 jet was simulated by direct numerical solution of the compressible Navier-Stokes equations in a computational domain that included the near acoustic field. Reynolds stresses, two-point correlations, and turbulent energy spectra are computed and discussed. The sound field is highly directional and dominated by Mach waves as are commonly observed experimentally. Analysis of the sound using weak-shock theory shows that non-linear effects are significant away from the jet, but that linear theory is sufficient to estimate near-field sound pressure levels. Sound pressure levels are compared with experimental results and are found to agree very well with jets at similar convective Mach numbers.

Original languageEnglish (US)
DOIs
StatePublished - Jan 1 1998
Externally publishedYes
Event4th AIAA/CEAS Aeroacoustics Conference, 1998 - Toulouse, France
Duration: Jun 2 1998Jun 4 1998

Other

Other4th AIAA/CEAS Aeroacoustics Conference, 1998
CountryFrance
CityToulouse
Period6/2/986/4/98

ASJC Scopus subject areas

  • Electrical and Electronic Engineering
  • Aerospace Engineering

Fingerprint Dive into the research topics of 'Direct simulation of a Mach 1.92 jet and its sound field'. Together they form a unique fingerprint.

  • Cite this

    Freund, J. B., Lele, S. K., & Moin, P. (1998). Direct simulation of a Mach 1.92 jet and its sound field. Paper presented at 4th AIAA/CEAS Aeroacoustics Conference, 1998, Toulouse, France. https://doi.org/10.2514/6.1998-2291