AustralieFrV1, Main, Exploration, bibRecord, 00D134

The feedback loop in impinging two-dimensional high-subsonic and supersonic jets

Identifieur interne : 00D134 ( Main/Exploration ); précédent : 00D133; suivant : 00D135

The feedback loop in impinging two-dimensional high-subsonic and supersonic jets

Auteurs : K. Hourigan [Australie] ; M. Rudman [Australie] ; E. Brocher [France]

Source :

Experimental Thermal and Fluid Science [ 0894-1777 ] ; 1996.

RBID : ISTEX:3C83C2564A857C036A607BD8271F71C8092404AE

Descripteurs français

Wicri :
- topic : Simulation.

English descriptors

Abstract

Abstract: The instabilities in a supersonic impinging jet are investigated by solving the two-dimensional Euler equations using the piecewise parabolic method (PPM) and Roe's linearized Riemann solver. The predicted shock cell spacing agrees well with the observed and theoretical values. The frequency and nature of the dominant instabilities are found to be a function of the impingement distance. Two instability modes are possible: a symmetric (or varicose) mode and an asymmetric (or sinuous) mode. For two given jet exit Mach numbers (M = 0.98 and 1.29), the energy in, and frequency of, these modes are functions of impingement distance, leading to an integral staging due to an acoustic feedback loop. The predicted frequencies of the fundamental symmetric and asymmetric instabilities agree with the theoretically allowed values. The staging of predicted frequencies that occurs in experimental work is also predicted.

Url:

https://api.istex.fr/document/3C83C2564A857C036A607BD8271F71C8092404AE/fulltext/pdf

DOI: 10.1016/0894-1777(95)00084-4

Affiliations:

Links toward previous steps (curation, corpus...)

to stream Istex, to step Corpus: 000B36
to stream Istex, to step Curation: 000B36
to stream Istex, to step Checkpoint: 002539
to stream Main, to step Merge: 00E296
to stream Main, to step Curation: 00D134

Le document en format XML

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<term>Acoustic feedback loop</term>
<term>Acoustic waves</term>
<term>Arbitrary units</term>
<term>Cold jets</term>
<term>Euler equation solution</term>
<term>Euler equations</term>
<term>Exit mach numbers</term>
<term>External flow</term>
<term>Feedback</term>
<term>Feedback loop</term>
<term>Flow variables</term>
<term>Fluid mech</term>
<term>Frequency figure</term>
<term>Grid</term>
<term>Impingement</term>
<term>Impingement distance</term>
<term>Impingement distances</term>
<term>Impingement tones</term>
<term>Industrial research organisation</term>
<term>Instability</term>
<term>Instability modes</term>
<term>Instability waves</term>
<term>Instantaneous flow</term>
<term>Linearized riemann solver</term>
<term>Loop strouhal number</term>
<term>Loop velocity</term>
<term>Mach</term>
<term>Mach number</term>
<term>Mach numbers</term>
<term>Nonlinear flux operator</term>
<term>Parabolic method</term>
<term>Power spectra</term>
<term>Pressure waves</term>
<term>Shock cell length</term>
<term>Simulation</term>
<term>Sound waves</term>
<term>State vector</term>
<term>Subsonic</term>
<term>Subsonic jets</term>
<term>Supersonic</term>
<term>Supersonic case</term>
<term>Supersonic jets</term>
<term>Symmetric mode</term>
<term>Theoretical analysis</term>
<term>Transverse direction</term>
<term>Unit mass</term>
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<term>Impingement distances</term>
<term>Impingement tones</term>
<term>Industrial research organisation</term>
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<term>Mach number</term>
<term>Mach numbers</term>
<term>Nonlinear flux operator</term>
<term>Parabolic method</term>
<term>Power spectra</term>
<term>Pressure waves</term>
<term>Shock cell length</term>
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<term>Theoretical analysis</term>
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<front><div type="abstract" xml:lang="en">Abstract: The instabilities in a supersonic impinging jet are investigated by solving the two-dimensional Euler equations using the piecewise parabolic method (PPM) and Roe's linearized Riemann solver. The predicted shock cell spacing agrees well with the observed and theoretical values. The frequency and nature of the dominant instabilities are found to be a function of the impingement distance. Two instability modes are possible: a symmetric (or varicose) mode and an asymmetric (or sinuous) mode. For two given jet exit Mach numbers (M = 0.98 and 1.29), the energy in, and frequency of, these modes are functions of impingement distance, leading to an integral staging due to an acoustic feedback loop. The predicted frequencies of the fundamental symmetric and asymmetric instabilities agree with the theoretically allowed values. The staging of predicted frequencies that occurs in experimental work is also predicted.</div>
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The feedback loop in impinging two-dimensional high-subsonic and supersonic jets

The feedback loop in impinging two-dimensional high-subsonic and supersonic jets

Source :

Descripteurs français

English descriptors

Abstract

Links toward previous steps (curation, corpus...)

Le document en format XML

Pour manipuler ce document sous Unix (Dilib)

Pour mettre un lien sur cette page dans le réseau Wicri