Numerical investigation of the noise generated by a rocket engine at lift-off conditions using a two-way coupled CFD-CAA method

Langenais, Adrien; Vincent, François; Troyes, Julien; Bailly, Christophe

doi:10.2514/6.2017-3212

Cited by 12 publications

(30 citation statements)

References 16 publications

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“…Williams & Hawkings and a full Euler computations. 44 The FWH method overestimates the far field noise by about 2 dB at 40D in the peak direction. These evidences clearly indicate that nonlinear propagation effects cannot be ignored in the far field.…”

Section: Similar Trends Have Been Observed By Comparing a Ffowcsmentioning

confidence: 96%

“…A microphone arc of ra- 45 The acoustic far field was computed with the Ffowcs Williams & Hawkings method. 31 More recently, Langenais et al 44 have adapted the case by using an identical near field mesh and computing the far field with the full Euler equations. Resulting aerodynamic and acoustic fields provide a valuable numerical database which will be referred as Langenais 2017 44 in the following.…”

Section: Experimental and Numerical Databasementioning

confidence: 99%

“…The full convergentdivergent nozzle geometry is explicitly included in the domain. Qualitatively based on a previous flow solution, 44 the coupling interface radius is chosen as r = 2.7x + 3.8 in order to follow the jet expansion. The ground is not included in the domain which extends 33.5D upstream, 81.6D downstream and 59.4D laterally.…”

Section: Computational Set-upmentioning

confidence: 99%

“…The azimuthal resolution at the nozzle lips has been found to significantly influence the early shear layer development. More recently, the far field mesh of a same free jet case 45 has been adapted by Langenais et al 44 to perform a Navier-Stokes−Euler coupled computation following the procedure described in section II B 3. Since the near field mesh and flow solution were unchanged, it has allowed to specifically study the impact of the nonlinearities on the acoustic far field.…”

Section: Past Effortsmentioning

confidence: 99%

“…The hexahedra at the nozzle lips provide an azimuthal resolution of about 2π/∆θ ≃ 1300 cells which is nearly three times the resolution of the previous grid. 44 The axial variation of d cell inside the nozzle boundary layer and along the lipline in the shear layer is plotted in Figure 2. The drop at x = 0 can be explained by the transition between hexahedral and tetrahedral elements.…”

Section: Present Improvementmentioning

confidence: 99%

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Accurate simulation of the noise generated by a hot supersonic jet including turbulence tripping and nonlinear acoustic propagation

et al. 2019

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A procedure to accurately simulate a free hot supersonic jet and its associated noise, which uses simultaneously a turbulence tripping method and a two-way coupling between a flow solver and a nonlinear acoustic solver, is proposed in this study. A Mach 3.1 overexpanded hot jet is computed via a large-eddy simulation by solving the filtered Navier-Stokes equations with a finite volume method on unstructured grids. The resulting noise is propagated in the far field by solving the full Euler equations with a high-order discontinuous Galerkin method on unstructured grids. The full convergent-divergent nozzle is explicitly included in the computational domain thanks to the unstructured flow solver. Both a refined grid and a geometrical boundary layer tripping in the convergent are used to get highly disturbed turbulent conditions at the nozzle lips. The flow field appears to agree with the expected turbulence behavior and the available experimental data. The jet development shows significant improvement compared to similar past simulations. The far field acoustic levels are finely recovered at most of observation angles. An analysis of the acoustic near and far fields is then performed. The studied conditions lead to strong shock-associated noise and Mach wave emission. The spatio-frequency and azimuthal content of the acoustic field is described in order to identify the main noise properties. A particular noise component, different from screech tones and radiating upstream like Mach waves, is highlighted. Nonlinear propagation effects are finally quantified through specific metrics. They are found significant in both the near and the far fields which justifies the use of a nonlinear acoustic solver.

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Section: Similar Trends Have Been Observed By Comparing a Ffowcsmentioning

confidence: 96%

Section: Experimental and Numerical Databasementioning

confidence: 99%

Section: Computational Set-upmentioning

confidence: 99%

Section: Past Effortsmentioning

confidence: 99%

Section: Present Improvementmentioning

confidence: 99%

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Accurate simulation of the noise generated by a hot supersonic jet including turbulence tripping and nonlinear acoustic propagation

et al. 2019

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Reduced-order model of a reacting, turbulent supersonic jet based on proper orthogonal decomposition

Alomar

Nicole

Sipp

et al. 2020

Theor. Comput. Fluid Dyn.

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Assessment of a Two-Way Coupling Methodology Between a Flow and a High-Order Nonlinear Acoustic Unstructured Solvers

Langenais

Vincent

Peyret

et al. 2018

Flow Turbulence Combust

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A two-way coupling on unstructured meshes between a flow and a high-order acoustic solvers for jet noise prediction is considered. The flow simulation aims at generating acoustic sources in the near field while the acoustic simulation solves the full Euler equations, thanks to a discontinuous Galerkin method, in order to take into account nonlinear acoustic propagation effects. This methodology is firstly validated on academic cases involving nonlinear sound propagation, shock waves and convection of aerodynamic perturbations. The results are compared to analytical solutions and direct computations. A good behaviour of the coupling is found regarding the targeted space applications. An application on a launch pad model is then simulated to demonstrate the robustness and reliability of the present approach.

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Numerical investigation of the noise generated by a rocket engine at lift-off conditions using a two-way coupled CFD-CAA method

Cited by 12 publications

References 16 publications

Accurate simulation of the noise generated by a hot supersonic jet including turbulence tripping and nonlinear acoustic propagation

Accurate simulation of the noise generated by a hot supersonic jet including turbulence tripping and nonlinear acoustic propagation

Reduced-order model of a reacting, turbulent supersonic jet based on proper orthogonal decomposition

Assessment of a Two-Way Coupling Methodology Between a Flow and a High-Order Nonlinear Acoustic Unstructured Solvers

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