Resolution of Computational Aeroacoustics Problems on Unstructured Grids with Splitting Method of Low Mach Number Flows

2011 ◽  
Author(s):  
Daming Ni ◽  
Wenping Zhang ◽  
Pingjian Ming ◽  
Meng Zhang
Keyword(s):  
Mach Number ◽  
Unstructured Grids ◽  
Splitting Method ◽  
Computational Aeroacoustics ◽  
Low Mach Number

Practical Computational Aeroacoustics for Compact Surfaces in Low Mach Number Flows

2011 ◽  
Vol 97 (1) ◽  
pp. 14-23 ◽  
Author(s):  
Ainara Pradera-Mallabiabarrena ◽  
Graeme Keith ◽  
Finn Jacobsen ◽  
Alejandro Rivas ◽  
Nere Gil-Negrete
Keyword(s):  
Mach Number ◽  
Computational Aeroacoustics ◽  
Low Mach Number ◽  
Compact Surfaces

A Splitting Method for Aeroacoustic Noise Prediction of Low Mach Number Viscous Flows

2005 ◽  
Vol 4 (1-2) ◽  
pp. 21-36 ◽  
Author(s):  
Young J. Moon ◽  
J. H. Seo
Keyword(s):  
Reynolds Number ◽  
Mach Number ◽  
Computational Efficiency ◽  
Plate Thickness ◽  
Splitting Method ◽  
Viscous Flows ◽  
Noise Prediction ◽  
Acoustic Analogy ◽  
Low Mach Number ◽  
Aeroacoustic Noise

A set of perturbed compressible equations(PCE), based on a hydrodynamic/acoustic splitting method, is proposed for aeroacoustic noise prediction of low Mach number viscous flows. The present formulation corrects the deficiency of previous splitting methods that have no control over the coupling effects between the incompressible vorticity and the perturbed velocities. The validation test shows that the present PCE solution is in excellent agreement with those of direct acoustic numerical simulation(DaNS) and Curle's acoustic analogy for a laminar dipole tone from a 2D circular cylinder at Reynolds number based on the cylinder diameter, ReD=200 and free stream Mach number, M∞ = 0.3. Computational efficiency and accuracy requirements for PCE are also investigated for a vortex scattering noise from the trailing-edge of a thin plate at Reynolds number based on the plate thickness, Reh= 2000 and M∞ = 0.3. The test results indicate that the computational efficiency can be achieved with an acoustic grid at lower resolution, as long as the projection quality of the total derivative of the incompressible pressure, DP/Dt field is retained.

Practical Computational Aeroacoustics for Complex Confined Scattering Geometries in Low Mach Number Flows

2013 ◽  
Vol 99 (1) ◽  
pp. 130-138 ◽  
Author(s):  
Ainara Pradera-Mallabiabarrena ◽  
Finn Jacobsen ◽  
Christian Svendsen ◽  
Alejandro Rivas ◽  
Nere Gil-Negrete
Keyword(s):  
Mach Number ◽  
Computational Aeroacoustics ◽  
Low Mach Number
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