Noise generation mechanisms for a supersonic jet impinging on an inclined plate

Christoph Brehm, Jeffrey A. Housman, Cetin C. Kiris

Research output: Contribution to journalArticlepeer-review

53 Scopus citations

Abstract

Noise generation mechanisms for a perfectly expanded supersonic Mach number M=1.8 turbulent jet impinging on a 45° inclined plate are investigated for a Reynolds number of 1.6 × 106 employing a large-eddy simulation. Excellent comparisons with experimental acoustic far-field measurements and pressure measurements on the impingement plate are obtained. Two local maxima are identified in the far-field overall sound pressure levels in the 75° and 120° observer directions, which are associated with different noise generation mechanisms. The peak frequencies in the spectra with Strouhal numbers of St D 0:2 for 75° and St = 0.5 for 120° match the experimental measurements. The jet-impingement region generates pressure waves that propagate predominantly in the 120° observer direction. The noise generation in this region is attributed to vortex stretching and tearing during shear-layer impingement, and shock oscillations that are induced by the motion of downstream convected vortical flow structures. The second peak in the overall sound pressure distribution at 75° is associated with noise sources located in the wall jet. The noise generation in the wall jet is associated with supersonically convecting large-scale coherent flow structures that also interact with tail shocks in the wall jet causing large localized pressure fluctuations. Strongly coherent flow structures are identified by applying proper orthogonal decomposition (POD) to the unsteady flow field. The frequency characteristics of the most energetic POD modes are distinctly different based on which energy norm is chosen. The most energetic entropy-based POD modes contain a peak frequency of approximately St = 0.4-0.6, while the most energetic turbulent kinetic-energy-based POD modes appear to be dominated by lower-frequency content. The causality method, based on Lighthill's acoustic analogy, is used to link the acoustic noise signature to the relevant physical mechanisms in the source region. A differentiation is made between the application of normalized and non-normalized cross-correlation functions for noise source identification and characterization.

Original languageEnglish
Pages (from-to)802-850
Number of pages49
JournalJournal of Fluid Mechanics
Volume797
DOIs
StatePublished - Jun 25 2016

Bibliographical note

Publisher Copyright:
© Cambridge University Press 2016.

Keywords

  • aeroacoustics
  • jet noise
  • shock waves

ASJC Scopus subject areas

  • Condensed Matter Physics
  • Mechanics of Materials
  • Mechanical Engineering

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