Noise radiated from free and impinging hot supersonic jets

Varnier, Jean; Raguenet, Wilfrid; Gely, D.

doi:10.2514/6.1998-2206

Cited by 8 publications

(5 citation statements)

References 11 publications

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“…A source distribution and extrapolation technique are used to develop an empirical analysis within the accuracy of ±6 [dB] for the standard configurations. 2,3 Whereas Reynolds averaged Navier-Stokes (RANS) simulation is capable of achieving the potential core length of a supersonic jet, large eddy simulation (LES) techniques have received significant attention in the prediction of high-frequency propagation behavior. Haynes et al 4 and Bodony et al 5,6 suggested that it is necessary to conduct an LES when considering the discretization scheme, boundary conditions, and far-field prediction based on the acoustic analogy, that is, the Lighthill theory.…”

Section: Introductionmentioning

confidence: 99%

A study on an integrated aero-vibro-acoustic analysis procedure for a small-scale supersonic jet and surrounding thin plates

Joo

Park

Kang

et al. 2022

International Journal of Aeroacoustics

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The goal of this paper is to examine the computational approaches for predicting both of the overall sound pressure level (OASPL) at a few locations and acceleration power spectral density (APSD) of surrounding thin plates due to the aero-acoustic pressure generated by a cold jet with M = 1.8. First, computational fluid dynamics (CFD), particularly delayed detached eddy simulation, are applied to predict the OASPL at the near-field and compute the acoustic properties. Second, the linearized boundary element method (BEM), that is, the Helmholtz-Kirchhoff method is utilized to propagate the pressure and obtain the OASPL at the far-field. Finally, the finite element method is implemented to predict the APSD for a clamped thin plate based on the optimal triangle membrane element, discrete Kirchhoff triangle plate bending element, and Newmark- β time integration scheme. Using the present CFD and BEM, the OASPLs are compared with the experimental results measured by microphones at both the near- and far-fields, respectively. Moreover, APSDs are compared with the experimental results obtained by an accelerometer at a few different locations. Although OASPLs are overestimated because of the coarse meshes in the higher-angle area and low order scheme of the present CFD analysis, the present integrated aero-vibro-acoustic analysis is capable of predicting the OASPL and APSD generated by a cold jet with M = 1.8.

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Section: Introductionmentioning

confidence: 99%

A study on an integrated aero-vibro-acoustic analysis procedure for a small-scale supersonic jet and surrounding thin plates

Joo

Park

Kang

et al. 2022

International Journal of Aeroacoustics

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“…Since this time, multiple new datasets and modifications have been developed to augment the SP-8072 modeling framework. [2][3][4][5][6][7][8][9][10] This paper describes a data-based analysis of a key source-related input parameter for SP-8072, the laminar or potential core length, � � . Sound pressure distributions resultant from two characteristic length definitions, the original proposed by Eldred 1) and a modification proposed by Varnier, 3,4) are compared with measurements from four full-scale solid rocket motors.…”

Section: Introductionmentioning

confidence: 99%

Comparative Analysis of NASA SP-8072's Core Length with Full-Scale Rocket Data

James

Salton

Gee

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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Development of the next-generation space flight vehicles has prompted a renewed focus on rocket sound source characterization and near-field propagation modeling. Improved measurements of the sound near the rocket plume are critical for direct determination of the acoustical environment both in the near and far-fields. These measurements are also crucial inputs to empirical models and utilized in validating computational aeroacoustics models. NASA's SP-8072 acoustic load prediction model [K. M. Eldred, NASA SP-8072 (1971)] is a widely used empirical model for predicting liftoff acoustics. The model implements a Distributed Source Method, which predicts the loading as the sum of the radiated acoustic pressure field from each source distributed along the plume. In this paper, the resultant sound distributions are compared among the original core length definition in SP-8072, a modification proposed by Varnier [

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“…This modification is not unique to this analysis. It has been documented by Varnier,5,6 and used by several analysts since that time. For the Ares I analysis, a RANS CFD turbulence model was used to check and compare the sound power distributions of Varnier and Eldred.…”

Section: Summary and Future Workmentioning

confidence: 99%

“…• Eldred's approximation is too large for comparable results (2 < M e < 3) with horizontal rocket test data (Varnier, 1998). …”

Section: Introductionmentioning

confidence: 99%

Modifications to the NASA SP-8072 Distributed Source Method II for Ares I Lift-Off Environment Predictions

Haynes

Kenny

2009

15th AIAA/CEAS Aeroacoustics Conference (30th AIAA Aeroacoustics Conference)

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Noise radiated from free and impinging hot supersonic jets

Cited by 8 publications

References 11 publications

A study on an integrated aero-vibro-acoustic analysis procedure for a small-scale supersonic jet and surrounding thin plates

A study on an integrated aero-vibro-acoustic analysis procedure for a small-scale supersonic jet and surrounding thin plates

Comparative Analysis of NASA SP-8072's Core Length with Full-Scale Rocket Data

Modifications to the NASA SP-8072 Distributed Source Method II for Ares I Lift-Off Environment Predictions

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