Aircraft Cabin Outflow Valve Tonal and Broadband Noise Prediction Using the Lattice Boltzmann Method

2017 ◽  
Author(s):  
Yoonshik Shin ◽  
Francesco Polidoro ◽  
Ignacio Gonzalez-Martino ◽  
Damiano Casalino
Keyword(s):  
Lattice Boltzmann Method ◽  
Lattice Boltzmann ◽  
Broadband Noise ◽  
Noise Prediction ◽  
Aircraft Cabin ◽  
Boltzmann Method

Turbofan Broadband Noise Prediction Using the Lattice Boltzmann Method

AIAA Journal ◽  
2018 ◽  
Vol 56 (2) ◽  
pp. 609-628 ◽  
Author(s):  
D. Casalino ◽  
A. Hazir ◽  
A. Mann
Keyword(s):  
Lattice Boltzmann Method ◽  
Lattice Boltzmann ◽  
Broadband Noise ◽  
Noise Prediction ◽  
Boltzmann Method

Large-Scale Numerical Simulation of Unsteady Flow Field in a Half-Ducted Propeller Fan Using Lattice Boltzmann Method

2015 ◽  
Author(s):  
Kazutoyo Yamada ◽  
Kazuya Kusano ◽  
Masato Furukawa
Keyword(s):  
Numerical Simulation ◽  
Flow Field ◽  
Lattice Boltzmann Method ◽  
Acoustic Field ◽  
Lattice Boltzmann ◽  
Large Scale ◽  
Broadband Noise ◽  
Experimental Result ◽  
Ducted Propeller ◽  
Boltzmann Method

Recently, the lattice Boltzmann method (LBM) is being applied in turbomachinery field, regarded as a good candidate for tool of flow simulation as well as aerodynamic sound analysis. For better prediction of broadband noise with high frequecy, which is generally generated in high Reynolds number flows, not only high grid resolution is required to capture very small eddies of the sound source inside the turbulent boundary layer, but also the computation of acoustic field is often needed. In such case, the direct simulation of flow field and acoustic field is straight-forward and effective. However, the computational cost becomes extremely expensive. Moreover, for low Mach number flows the compressible Navier-Stokes simulation not only requires high-order scheme which is unsuitable for parallel computation, but also suffers from stiff problem. LBM is suitable for such simulation thanks to its advantages. In the present study, a large-scale numerical simulation of flow field around a half-ducted propeller fan is conducted with LBM, and its result is validated by comparing with the experimental result.

Direct Numerical Simulation of Turbulent Flow and Aeroacoustic Fields Around an Airfoil Using Lattice Boltzmann Method

2016 ◽  
Author(s):  
Kazuya Kusano ◽  
Kazutoyo Yamada ◽  
Masato Furukawa ◽  
Kil-Ju Moon
Keyword(s):  
Numerical Simulation ◽  
Boundary Layer ◽  
Reynolds Number ◽  
Direct Numerical Simulation ◽  
Lattice Boltzmann Method ◽  
Lattice Boltzmann ◽  
Separated Flow ◽  
Broadband Noise ◽  
Suction Surface ◽  
Boltzmann Method

The paper presents a result of the direct numerical simulation with the lattice Boltzmann method which was conducted for quantitative prediction of turbulent broadband noise. For better prediction of broadband noise with high frequency, which is generally generated in high Reynolds number flows, not only high grid resolution is required for a flow simulation to capture very small eddies of the sound source inside the turbulent boundary layer, but also the computation of acoustic field is often needed. In such case, the direct simulation of flow field and acoustic field is straightforward and effective. In this study, the direct simulation with the lattice Boltzmann method was conducted for a flow around the NACA0012 airfoil with the Reynolds number of two hundred thousand. In order to efficiently simulate this high Reynolds number flow with the LBM, the multi-scale approach was introduced in conjunction with the Building-cube method, while keeping the advantage of the LBM with the Cartesian mesh. At the condition with angle-of-attack of 9 degrees, a laminar separation bubble arises on the suction surface near the leading-edge and the suction boundary layer downstream of it is turbulent due to the separated-flow transition. As a result, turbulent broadband noise is generated from the boundary layer over the airfoil with the separated-flow transition. In the paper, as for prediction of such broadband noise, the computed frequency spectrum of far-field sound is validated to agree with the experimental result. In addition, through the detailed analyses of turbulent properties of the turbulent boundary layer on the suction surface, the validity of the present direct numerical simulation is demonstrated.

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