Comprehensive 3D Unsteady Simulations of Subsonic and Supersonic Hot Jet Flow-Fields: Part 2: Acoustic Analysis

Biancherin, Anthoine; Lupoglazoff, Nicols; Rahier, Gilles; Vincent, François

doi:10.2514/6.2002-2600

Cited by 20 publications

(11 citation statements)

References 10 publications

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“…8 and 9, Bodony and Lele [10], Andersson, Eriksson and Davidson [11], Loh, Himansu and Hultgren [12], a triplet of papers by the ONERA group (Refs. [13][14][15] and twin studies of Uzun et al [16] and Lew et al [17]. Early versions of the present effort are in Refs.…”

Section: State Of the Artmentioning

confidence: 99%

Noise Prediction for Increasingly Complex Jets. Part I: Methods and Tests

Shur

Spalart

Strelets

2005

International Journal of Aeroacoustics

306

250

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This Part I presents a detailed description of a numerical system built and tested with the final goal of reaching an accuracy of 2–3 dB over a meaningful range of frequencies for airliner engine noise, while having low empiricism and a general-geometry capability. The turbulence is treated by Large-Eddy Simulation with grids of around 1 million points, slightly upwind-biased high-order differencing, and implicit time integration. The code can incorporate boundaries and multi-block grids (thus avoiding the centerline singularity), and capture shocks. The sub-grid scale model is de-activated, because on present grids it strongly interferes with transition in the mixing layer. Without unsteady inflow forcing, the shear-layer roll-up and three-dimensionalization are realistic and reasonably insensitive to the grid. The far-field noise is computed using the permeable Ffowcs-Williams/Hawkings (FWH) formulation without external quadrupoles. The treatment of the disk that closes the FWH surface near the outflow must be approximate, since the turbulent region is unbounded, and is crucial; it benefits from a change of variable from density to pressure, and other mitigating steps. Tests are presented in support of the key elements of the strategy. In a simple isothermal jet, the system is close to the 2–3 dB target both in terms of directivity and of spectrum, up to a Strouhal number of about 1.5. In Part II, the following effects are explored with overall success: jet Mach numbers from 0.3 to slightly supersonic with under-expansion (generating shock cells), jet heating, co-flow, and “synthetic chevrons.”

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Section: State Of the Artmentioning

confidence: 99%

Noise Prediction for Increasingly Complex Jets. Part I: Methods and Tests

Shur

Spalart

Strelets

2005

International Journal of Aeroacoustics

306

250

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“…Advancements in computational performance and CAA have made numerical simulation methods better suited to jet noise research [12][13][14][15][16][17][18][19][20]. e muzzle noise production and development mechanism has also been researched using CFD-CAA hybrid methods [21][22][23][24].…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation and Experiment on Impulse Noise in a Small Caliber Rifle with Muzzle Brake

Zhao

Zhou

et al. 2019

Shock and Vibration

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Blast waves generated from the muzzles of weapons may exert negative effects, such as shock waves and impulse noise. If the weapon is fired with a muzzle brake, these effects are recognized to be more severe. This paper discusses the influence of the muzzle brake on certain aeroacoustic noise characteristics based on numerical simulations and a corresponding experiment. The impulse noise, which is induced by complex jet flows discharging from small caliber rifles with muzzle brakes, is focused in this study. Computational fluid dynamics (CFD) and computational aeroacoustics (CAA) are combined to calculate the muzzle flow field and jet noise for cases with and without a muzzle brake, and then the data sets are carefully compared. The simulations indicate that the muzzle brake alters the muzzle flow field and directional distribution of the jet noise compared to a rifle sans muzzle brake. Deviations less than 7.6% between experimental data and simulation results validate the simulation model. The results presented in this paper may provide a workable reference for the prediction of muzzle noise and the optimization of muzzle brake designs.

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“…No turbulence seeding is made in the boundary layers. Several experimental [19][24] and numerical investigations [10][18]- [20][22] [25] [26] in the past were carried out on this jet configuration and experimental data are available for comparison with simulation results. The paper is organized as follows.…”

Section: Introductionmentioning

confidence: 99%