Numerical Aspects of Rocket Lift-off Noise with Launch-Pad Aqueous Injection

Salehian, Saman; Kourbatski, Konstantine; Golubev, Vladimir V.; Mankbadi, Reda R.

doi:10.2514/6.2018-0519

Cited by 10 publications

(5 citation statements)

References 18 publications

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“…The results in the present work were calculated using the control parameter set to 0.25 which has been found to be optimal. This differentiates current results from those reported in earlier works 4–7 which were calculated using the strict BCD as this was the only BCD formulation available in the code at that time.…”

Section: Numerical Modelsupporting

confidence: 41%

“…This study presents an extension of the previous works [4][5][6][7] on numerical simulation of mean flow and acoustic radiation of an impinging supersonic jet. The focus of investigations 4,5 was on the validation of numerical approaches and establishing best practices to analyze supersonic jet impingement noise in the framework of the general-purpose CFD solver Ansys Fluent.…”

Section: Introductionmentioning

confidence: 89%

“…8 The effects of inclination angle on mean flow and noise radiation from an impinging jet were presented in publication. 6 A simulation approach 7 to the problem of mitigating impinging jet noise by aqueous injections presented a novel multiphase modeling methodology capable of including water jet injections into the supersonic flow.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Numerical prediction of mean flow and acoustic field of a supersonic impinging jet

Kourbatski

2024

International Journal of Aeroacoustics

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The three-dimensional turbulent mean flow and acoustic field of a supersonic jet impinging on a solid plate is studied computationally using the general purpose CFD code Ansys Fluent. A pressure-based coupled solver formulation with the second order weighted central-upwind spatial discretization is applied to compute transient solutions. Cold and hot jet thermal conditions are considered. Mean flow characteristics are investigated by a steady-state modeling approach. Acoustic radiation of impingement tones is simulated using a transient time-domain formulation. The effects of turbulence in steady-state are modeled by the SST k-ω turbulence model. The Wall-Modeled Large-Eddy Simulation (WMLES) model is applied to compute transient solutions. The near-wall mesh on the impingement plate is fine enough to resolve the viscosity-affected near-wall region all the way to the laminar sublayer. Nozzle-to-plate distance is parameterized in the model for automatic re-generation of the mesh and results. Steady-state predictions of hover lift loss and mean jet velocity distributions are compared with experimental data, and favorable agreement is reported. The transient solution reproduces the mechanism of impingement tone generation by the interaction of large scale vortical structures with the impingement plate. The acoustic near-field is directly resolved by Computational Aeroacoustics (CAA) to accurately propagate impingement tone waves to near-field microphone locations. Calculated impingement tone frequencies and sound pressure levels agree with experimental values.

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Section: Numerical Modelsupporting

confidence: 41%

Section: Introductionmentioning

confidence: 89%

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Numerical prediction of mean flow and acoustic field of a supersonic impinging jet

Kourbatski

2024

International Journal of Aeroacoustics

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“…The maximum resolvable frequency is calculated based on the assumption that a minimum of 15 points (cells) per wavelength are required to capture the acoustic waves up to = 0.35 with the current numerical scheme. Such a requirement has been tested for the prediction of waves using second-order finite volume schemes when applied to hexahedral cells [73]. The volumetric flux across a face is split into two components of f + and f −, which are evaluated based on the cell values on either side of the face.…”

Section: Numerical Approachmentioning

confidence: 99%

Jet Noise in Airframe Integration and Shielding

Salehian

Mankbadi

2020

Applied Sciences

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This paper reviews and presents new results on the effect of airframe integration and shielding on jet noise. Available experimental data on integration effects are analyzed. The available options for the computation of jet noise are discussed, and a practical numerical approach for the present topic is recommended. Here, it is demonstrated how a hybrid large eddy simulation—unsteady Reynolds-averaged Navier-Stokes approach can be implemented to simulate the effect of shielding on radiated jet noise. This approach provides results consistent with the experiment and suggests a framework for studying more complex geometries involving airframe integration effects.

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“…These designs include, but are not limited to, the use of oblique impingement [5,6], the installation of front-covers within the vertical flame path [7] and the introduction of a wall with a circular cut-out to block the upstream traveling waves from the impingement area towards the nozzle lip [8]. Active noise reduction methods on the other hand, often focus on fluid injection at certain strategic locations around the nozzle exit and beneath the impingement plate [9][10][11][12]. Although these approaches have enjoyed some measure of success, a more systematic study of the sensitivity of an impinging jet flow-field to different types of actuators forcing is lacking.…”

Section: Introductionmentioning

confidence: 99%