On LAGOON Nose Landing Gear CFD/CAA Computation over Unstructured Mesh using a ZDES approach

Puente, Fernando de la; Sanders, Laurent; Vincent, François

doi:10.2514/6.2014-2763

Cited by 18 publications

(24 citation statements)

References 12 publications

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“…To predict the far-field noise from obtained 2D near-field flow data, the missing data along the span can be compensated by assigning an SCL. For a variety of bluff body shapes at moderate to high Re, the flow was found to be fully correlated just along a few body diameters [39,[41][42][43].…”

Section: Proposed Approach For the Lg Far-field Noise Predictionmentioning

confidence: 95%

Predicting Far-Field Noise Generated by a Landing Gear Using Multiple Two-Dimensional Simulations

2019

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Featured Application: Far-field noise prediction of flow past complex multi-component structures. Abstract: In this paper, a new approach is proposed to predict the far-field noise of a landing gear (LG) based on near-field flow data obtained from multiple two-dimensional (2D) simulations. The LG consists of many bluff bodies with various shapes and sizes. The analysis begins with dividing the LG structure into multiple 2D cross-sections (C-Ss) representing different configurations. The C-Ss locations are selected based on the number of components, sizes, and geometric complexities. The 2D Computational Fluid Dynamics (CFD) analysis for each C-S is carried out first to obtain the acoustic source data. The Ffowcs Williams and Hawkings acoustic analogy (FW-H) is then used to predict the far-field noise. To compensate for the third dimension, a source correlation length (SCL) is assumed based on a perfectly correlated flow. The overall noise of the LG is calculated as the incoherent sum of the predicted noise from all C-Ss. Flow over a circular cylinder is then studied to examine the effect of the 2D CFD results on the predicted noise. The results are in good agreement with reported experimental and numerical data. However, the Strouhal number (St) is over-predicted. The proposed approach provides a reasonable estimation of the LG far-field noise at a low computational cost. Thus, it has the potential to be used as a quick tool to predict the far-field noise from an LG during the design stage.The direct numerical simulation (DNS) of complex three-dimensional (3D) aircraft systems, such as the LGs, is computationally expensive. This is because the 3D model needs high spatial and temporal resolutions to resolve the wide range of energy and length scales between the flow and acoustic fields. Therefore, an efficient two-step hybrid computational aeroacoustics (CAA) approach was proposed, where the flow and the acoustic fields are computed using two independent solvers [8]. In the last decade, noise generated due to flow past a simplified LG geometry has been extensively investigated using hybrid CAA approaches. The numerical results were validated with experiments through benchmark problems for airframe noise computations (BANC) workshops [10][11][12][13][14]. The BANC workshops focus on improving the far-field noise prediction accuracy of the 3D simulations and reducing the computation time. There are a few semi-empirical tools developed to facilitate the noise prediction of the LG during the design stage [3,7]. Among these, the Landing Gear Model and Acoustic Prediction tool (LGMAP) has been developed for a quick noise estimate of the LG [15]. However, lower fidelity approaches are essential to predict the flow and acoustic quantities with better computational efficiency and reasonable accuracy.The two-dimensional (2D) Computational Fluid Dynamics (CFD) analysis provides a faster way to predict the near-field data. A few studies investigated the validity of the 2D simulations to predict the far-field noise of the flow...

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Section: Proposed Approach For the Lg Far-field Noise Predictionmentioning

confidence: 95%

Predicting Far-Field Noise Generated by a Landing Gear Using Multiple Two-Dimensional Simulations

2019

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“…The present computation is based on a previous computation performed with the CEDRE code on the same geometry, presented in reference [12]. A second hybrid grid is constructed based on the previous one, re-arranging the elements of the grid in order to obtain a refined grid with the same mesh metrics, hence the computational cost is expected to be comparable.…”

Section: Mesh Generationmentioning

confidence: 99%

Zonal Detached Eddy Simulation of a simplified nose landing-gear for flow and noise predictions using an unstructured Navier-Stokes solver

Cerezo

Sanders

Vincent

et al. 2017

Journal of Sound and Vibration

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“…However, the RANS/LES method is still very expensive for aeroacoustic prediction because of the large amount of high-resolved grids and long-time cost required by the LES simulation. A well-known benchmark study for a 2-wheel gear named LAGOON showed the comparisons between different CFD solvers for aeroacoustic 2 Mathematical Problems in Engineering prediction [3,9]. So how to predict the aeroacoustics with more efficiency with good accuracy is a challenging task.…”

Section: Introductionmentioning

confidence: 99%

“…There are mainly four types of numerical aeroacoustic prediction methods [5], including the pure theoretical method [6], the semiempirical method [7], the direct numerical method, and the hybrid method [3,8]. In particular, the Lattice-Boltzmann-Method (LBM) has shown being a very promising technique for far field aeroacoustic prediction (Benjamin Duda, Ehab Fares, 2017), such as LAGOON landing-gear configuration [9] and Jet-plate interaction noise [10].…”

Section: Introductionmentioning

confidence: 99%

“…For example, the airfoil self-noise is one of the main noise sources which is induced by the interactions between the airfoil blade and the turbulence flow produced by its own boundary layer and near wake [1]. The strong interactions between the vortex from the upstream flow and the airfoils downstream are one of the most important effects in airframe noise generation, especially in the aircraft take-off and landing on the ground [2][3][4].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Numerical Investigation on Vortex‐Structure Interaction Generating Aerodynamic Noises for Rod‐Airfoil Models

Liu

Jiang

Chen

et al. 2017

Mathematical Problems in Engineering

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In past several decades, vortex-structure interaction generated aerodynamic noise became one of the main concerns in aircraft design. In order to understand the mechanism, the acoustic analogy method combined with the RANS-based nonlinear acoustics solver (NLAS) is investigated. The numerical method is firstly evaluated by the experiment data of the classic rod-airfoil model. Compared with the traditional analogy methods, the RANS/NLAS can capture the nonlinear aerodynamic noise more accurately with lower gird requirements. Then different rod-airfoil configurations were simulated to investigate the aeroacoustic interaction effects. The numerical results are in good agreement with those of the earlier experimental research. It is found that the vortexshedding crash to the airfoil is the main reason for the noise generation which is dependent on the configurations, distance, and flow conditions.

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On LAGOON Nose Landing Gear CFD/CAA Computation over Unstructured Mesh using a ZDES approach

Cited by 18 publications

References 12 publications

Predicting Far-Field Noise Generated by a Landing Gear Using Multiple Two-Dimensional Simulations

Predicting Far-Field Noise Generated by a Landing Gear Using Multiple Two-Dimensional Simulations

Zonal Detached Eddy Simulation of a simplified nose landing-gear for flow and noise predictions using an unstructured Navier-Stokes solver

Numerical Investigation on Vortex‐Structure Interaction Generating Aerodynamic Noises for Rod‐Airfoil Models

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