12th AIAA/CEAS Aeroacoustics Conference (27th AIAA Aeroacoustics Conference) 2006
DOI: 10.2514/6.2006-2417
|View full text |Cite
|
Sign up to set email alerts
|

CAA Using 3D CESE Method with a Simplified Courant Number Insensitive Scheme

Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...
3
2

Citation Types

1
4
0

Year Published

2007
2007
2023
2023

Publication Types

Select...
2
2
1

Relationship

0
5

Authors

Journals

citations
Cited by 8 publications
(5 citation statements)
references
References 4 publications
1
4
0
Order By: Relevance
“…A 3D simulation was performed for the propagation of a Gaussian acoustic pulse and a vorticity wave embedded in a Mach 0.5 mean flow. Once again, the CESE results were in good agreement with the corresponding analytical solution in preserving both the form and amplitude of the waves [17]. Yen [18] further conducted a series of 3D CESE simulations for the Helmholtz resonator problem.…”
Section: Aeroacousticssupporting
confidence: 59%
See 1 more Smart Citation
“…A 3D simulation was performed for the propagation of a Gaussian acoustic pulse and a vorticity wave embedded in a Mach 0.5 mean flow. Once again, the CESE results were in good agreement with the corresponding analytical solution in preserving both the form and amplitude of the waves [17]. Yen [18] further conducted a series of 3D CESE simulations for the Helmholtz resonator problem.…”
Section: Aeroacousticssupporting
confidence: 59%
“…Additionally, the authors also pointed out that the non-reflecting boundary condition, which plays an important role in CAA, is much simpler to implement in the CESE method than in traditional methods (see [15,16]). To deal with practical multi-dimensional CAA problems where large disparity in grid cell size is inevitable, Yen et al [17,18] modified the Courant number insensitive (CNI)-CESE scheme [17] and the local time-stepping CESE scheme [18] to improve the numerical efficiency. A 3D simulation was performed for the propagation of a Gaussian acoustic pulse and a vorticity wave embedded in a Mach 0.5 mean flow.…”
Section: Aeroacousticsmentioning
confidence: 99%
“…The local CFL ν at the solution point Q * is defined to be the maximum value among ν 1 , ν 2 , ν 3 , ν 4 , ν 5 , ν 6 , ν 7 , and ν 8 . It should be pointed out that as with done to the tetrahedron grid by Yen et al (2006), we calculate the simplified grid CFL for only half time step marching instead of the formal grid CFL for a full Δt in order not to avoid incurring extra mesh management effort. The formal grid CFL for a full Δt involves the influencing cells for a solution point larger than the immediate neighboring cells, and the resulting grid CFL calculation is expensive and complex to apply for our large-scale parallel computation application of solar wind modeling with composite six-component grids.…”
Section: Courant-number Insensitive Methodsmentioning
confidence: 99%
“…For calculating the local CFL number ν, we use a simplified 3D grid CFL calculation as proposed by Yen et al (2006). The simplified 3D grid CFL, according to Yen et al (2006), is defined by enforcing the necessary condition of stability, namely, to require the analytical domain of dependence to be bounded by the numerical domain of dependence, associated with a solution point.…”
Section: Courant-number Insensitive Methodsmentioning
confidence: 99%
See 1 more Smart Citation