Internal:CDT3D SU2: Difference between revisions
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== General == | == General == | ||
* Oct 30 2018 presentation [http://www.cs.odu.edu/crtc/SU2/MeshGenMeeting_Oct30.pdf] | |||
* Pointwise and SU2 [https://blog.pointwise.com/2018/03/14/high-lift-prediction-using-su2-v6-falcon-pointwise/] | |||
* Paper : Construction of Prism and Hex Layers from Anisotropic Tetrahedra [https://arc.aiaa.org/doi/10.2514/6.2015-2296] see also [http://www.pointwise.com/theconnector/2017-Q1/Mesh-Generation-NASA-High-Lift-Common-Research-Model.html] | |||
== Interesting points from SU2 developers == | |||
* linear scalability is expected if there are at least 5000 grid points per core. [https://youtu.be/oEhlwbye90w?t=1186] | |||
== Refinement Regions == | |||
* Pointwise video [https://youtu.be/M1Tz5lPpynI?t=1512] | |||
=== BL discussion with Beckett === | |||
For the target method RANS+LES boundary layer is needed to resolve the turbulance. | For the target method RANS+LES boundary layer is needed to resolve the turbulance. | ||
Specifically for the Delta wing see thje link bellow for more details of the simulation. | Specifically for the Delta wing see thje link bellow for more details of the simulation. | ||
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* European Knowledge base for CFD simulations [http://www.kbwiki.ercoftac.org/w/index.php/Main_Page] | * European Knowledge base for CFD simulations [http://www.kbwiki.ercoftac.org/w/index.php/Main_Page] | ||
* Project page in the site above for the Delta wing case [http://www.kbwiki.ercoftac.org/w/index.php/CFD_Simulations_AC1-09] | * Project page in the site above for the Delta wing case [http://www.kbwiki.ercoftac.org/w/index.php/CFD_Simulations_AC1-09] | ||
= Delta Wing Project AIAA Aviation 2019 = | |||
Box Directory [https://odu.app.box.com/folder/60603354670] | |||
Gitlab project [https://git-community.cs.odu.edu/nikos/SU2-Project] | |||
Time required for the first mesh simulation (from Becket) : | |||
<blockquote> | |||
''I just checked the record: for 15 CTU in the periodic steady state region (where we compute mean flow and turbulent stats), it took 3 days and 7 hours on 480 processors. The transient is about another 10 CTUs and that took roughly another 2 days. '' | |||
''So in total: 25 CTUs for about 5 days. We are computing longer than the Go4Hybrid guys tho: they use 7+13=20CTU.'' | |||
</blockquote> | |||
presentation on the requirements of the next mesh | |||
Latest revision as of 05:22, 28 June 2019
General
- Oct 30 2018 presentation [1]
- Pointwise and SU2 [2]
- Paper : Construction of Prism and Hex Layers from Anisotropic Tetrahedra [3] see also [4]
Interesting points from SU2 developers
- linear scalability is expected if there are at least 5000 grid points per core. [5]
Refinement Regions
- Pointwise video [6]
BL discussion with Beckett
For the target method RANS+LES boundary layer is needed to resolve the turbulance. Specifically for the Delta wing see thje link bellow for more details of the simulation. During the fine-tunning of the mesh it it expected to require changes mostly in the boundary layer, since, this is where the turbulance near the boundary ( which we are trying to resolve) lives.
Boundary layer is usually given the following restrictions:
- Δs: Distance of first cell from the solid surface
- Thickness of the boundary layer
- Stretching factor / number of layers
More Links
- Open source tool for creating meshes https://www.salome-platform.org/
- European Knowledge base for CFD simulations [7]
- Project page in the site above for the Delta wing case [8]
Delta Wing Project AIAA Aviation 2019
Box Directory [9]
Gitlab project [10]
Time required for the first mesh simulation (from Becket) :
I just checked the record: for 15 CTU in the periodic steady state region (where we compute mean flow and turbulent stats), it took 3 days and 7 hours on 480 processors. The transient is about another 10 CTUs and that took roughly another 2 days.
So in total: 25 CTUs for about 5 days. We are computing longer than the Go4Hybrid guys tho: they use 7+13=20CTU.
presentation on the requirements of the next mesh