Shock-Refracted Acoustic Wave Model for Screech Amplitude in Supersonic Jets

Kandula, Max

doi:10.2514/1.30913

Cited by 14 publications

(12 citation statements)

References 43 publications

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“…In imperfectly expanded supersonic jets, additional noise is generated on account of broadband shock noise emanating from shockturbulence interaction and screech tones 5, with the tonal amplitude likely occasioned by shockacoustic wave interaction. 6 Scale models are often used in early design stage as a means of predicting the acoustic environment associated with flight vehicles. A detailed knowledge of the mechanisms of noise generation and noise radiation by jets is essential in designing a scale model of the noise source.…”

Section: F1 -Thrustmentioning

confidence: 99%

On the Scaling Laws and Similarity Spectra for Jet Noise in Subsonic and Supersonic Flow

Kandula¹

2008

IJAV

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The scaling laws for the simulation of noise from subsonic and ideally expanded supersonic jets are reviewed with regard to their applicability to deduce full-scale conditions from small-scale model testing. Important parameters of scale model testing for the simulation of jet noise are identified, and the methods of estimating full-scale noise levels from simulated scale model data are addressed.The limitations of cold-jet data in estimating high-temperature supersonic jet noise levels are discussed. New results are presented showing the dependence of overall sound power level on the jet temperature ratio at various jet Mach numbers. A generalized similarity spectrum is also proposed, which accounts for convective Mach number and angle to the jet axis.

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Section: F1 -Thrustmentioning

confidence: 99%

On the Scaling Laws and Similarity Spectra for Jet Noise in Subsonic and Supersonic Flow

Kandula¹

2008

IJAV

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“…With regard to the validity of the linear theory, Kandula [7] recently applied the linear theory to the production of screech noise, regarded as a consequence of interaction of an incident acoustic wave and a shock wave, and obtained a remarkable agreement with data for the screech amplitude for fully expanded Mach number M j up to 2. The predicted directivity pattern is also satisfactory when compared with measurements.…”

Section: Discussionmentioning

confidence: 98%

“…In perfectly expanded supersonic jets (nozzle exit plane pressure equals the ambient pressure), the large-scale mixing noise manifests itself primarily as Mach wave radiation [3,4] caused by the supersonic convection of turbulent eddies with respect to the ambient fluid. In imperfectly expanded supersonic jets (nozzle exit pressure different from the ambient pressure) typical of jet and rocket exhausts at offdesign conditions, additional noise is generated in the form of broadband shock-associated noise (BBSN) emanating from shock-turbulence interaction [5] and screech tones [6] with the tonal (screech) amplitude shown to be occasioned by shock-acoustic wave interaction [7]. Figure 1 displays a typical narrowband farfield shock noise spectrum, indicating various noise components.…”

Section: Introductionmentioning

confidence: 99%

A Theoretical Basis for the Scaling Law of Broadband Shock Noise Intensity in Supersonic Jets

Kandula

2011

Advances in Acoustics and Vibration

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A theoretical basis for the scaling of broadband shock noise intensity in supersonic jets was formulated considering linear shockshear wave interaction. Modeling of broadband shock noise with the aid of shock-turbulence interaction with special reference to linear theories is briefly reviewed. A hypothesis has been postulated that the peak angle of incidence (closer to the critical angle) for the shear wave primarily governs the generation of sound in the interaction process with the noise generation contribution from off-peak incident angles being relatively unimportant. The proposed hypothesis satisfactorily explains the well-known scaling law for the broadband shock-associated noise in supersonic jets.

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Section: Introductionmentioning

confidence: 99%

Simulation of Supersonic Jet Noise with Nonlinear CFD and Kirchhoff Surface Integral

Kandula

2008

Engineering Applications of Computational Fluid Mechanics

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An acoustic prediction capability for supersonic axisymmetric jets was developed on the basis of the OVERFLOW Navier-Stokes CFD (Computational Fluid Dynamics) code. Reynolds-averaged turbulent stresses in the flow field are modeled with the aid of Spalart-Allmaras one-equation turbulence model. Appropriate acoustic and outflow boundary conditions were implemented to compute time-dependent acoustic pressure in the nonlinear source-field. Based on the specification of acoustic pressure, its temporal and normal derivatives on the Kirchhoff surface, the near-field and the far-field sound pressure levels are computed via Kirchhoff surface integral, with the Kirchhoff surface chosen to enclose the nonlinear sound source region described by the CFD code. The method is validated by a comparison of the predictions of sound pressure levels with the available data for axisymmetric turbulent supersonic perfectly expanded jets.

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Shock-Refracted Acoustic Wave Model for Screech Amplitude in Supersonic Jets

Cited by 14 publications

References 43 publications

On the Scaling Laws and Similarity Spectra for Jet Noise in Subsonic and Supersonic Flow

On the Scaling Laws and Similarity Spectra for Jet Noise in Subsonic and Supersonic Flow

A Theoretical Basis for the Scaling Law of Broadband Shock Noise Intensity in Supersonic Jets

Simulation of Supersonic Jet Noise with Nonlinear CFD and Kirchhoff Surface Integral

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