A CFD/CAA coupling method applied to jet noise prediction

Labbé, O.; Peyret, Christophe; Rahier, Gilles; Huet, Maxime

doi:10.1016/j.compfluid.2013.07.013

Cited by 24 publications

(22 citation statements)

References 36 publications

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“…Harris et al 35,36 have overlapped an unstructured LES and a discontinuous Galerkin acoustic solver to run a 2D simulation of the Space Launch System acoustic environment. Labbé et al 37 have performed a one-way Navier-Stokes−Euler coupling for subsonic jet noise prediction. Results have been compared to those obtained from the Ffowcs Williams & Hawkings integral method and have agreed in linear regime as expected.…”

Section: Introductionmentioning

confidence: 99%

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: Introductionmentioning

confidence: 99%

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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“…have been firstly weakly coupled to the linearized Euler equations (LEE) as presented in the works of Djambozov et al [25] or Bogey et al [26]. More recently, one-way couplings between NS equations and full Euler equations have been performed as reported by Sescu et al [27] (2D subsonic and supersonic jet cases with structured solvers), Harris et al [28] (2D application to the SLS acoustic ambiance with unstructured solvers) or Labbé et al [29] (3D subsonic jet case with structured LES and unstructured Euler solver). In particular, Tsutsumi et al [17] have simulated an impinging jet inside various flame trench geometries thanks to a structured flow solver.…”

Section: Introductionmentioning

confidence: 99%

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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“…At each time step of the simulation, after solving (25) the domain Ω b has to be switched on and included for the computation of the incident acoustic pressure in (26), and then switched off to compute the diffracted sound field in (27). Besides, it should be noted that special care should be taken when interpolating the results from the CFD domain to the acoustic one to avoid spurious errors [43,44,45].…”

Section: Fully Discretized Numerical Scheme In Space and Timementioning

confidence: 99%

Concurrent finite element simulation of quadrupolar and dipolar flow noise in low Mach number aeroacoustics

et al. 2016

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The computation of flow-induced noise at low Mach numbers usually relies on a two-step hybrid methodolgy. In the first step, an incompressible fuid dynamics simulation (CFD) is performed and an acoustic source term is derived from it. The latter becomes the inhomegenous term for an acoustic wave equation, which is solved in the second step, often resorting to boundary integral formulations. In the presence of rigid bodies, Curle's acoustic analogy is probably the most extended approach. It has been shown that Curle's boundary dipolar noise contribution does in fact correspond to the diffraction of the quadrupolar aerodynamic noise generated by the flow past the rigid body. In this work, advantage is taken from this fact to propose an alternative computational methodology to get the individual quadrupolar and dipolar contributions to the total acoustic pressure. For any linear acoustic wave operator, the unknown acoustic pressure can be split into its incident and diffracted components and be computed simultaneously to the incompressible flow field, in a single finite element computational run. This circumvents the problem found in Curle's analogy of needing the total pressure at the body's boundary, which includes the acoustic pressure fluctuations. The latter cannot be obtained from an incompressible CFD simulation. The proposed unified strategy could be beneficial for a large variety problems such as those involving noise generated from duct terminations, or those related with the simulation of fricatives in numerical voice production, among many others.

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A CFD/CAA coupling method applied to jet noise prediction

Cited by 24 publications

References 36 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

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

Concurrent finite element simulation of quadrupolar and dipolar flow noise in low Mach number aeroacoustics

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