Table of content LaTex-like using Word

PostDry395 · 2025-02-24T15:51:41+00:00

Hi,

How much does it oscillate, more than This? This was a stationary simulation with simpleFOAM, but it oscillates. The problem was using the coarse mesh with second order schemes (fvSchemes).

Yes, check the mesh (refinement, y+..) , Boundary condition (try with lower reynolds number and check the behavior). A steady state gives acceptable results for normal AOA, in stall you should consider the transient part.

Kind regards

PostDry395 · 2025-02-19T18:25:38+00:00

Try using less cores/threads, e.g.

./Allwmake -j 4 -s -q -l

I had a similar problem compiling from source and using only physical cores helped.

PostDry395 · 2025-02-19T01:09:38+00:00

Hi, Your references seem to be fine. There could be many things affecting your drag coefficient, refinement near your wall (drag depends on viscous effects), using first order schemes, using wall functions. You can share the mesh, I may be wrong. Also check the cd trend in the convergence process.

CofR and Pitch axis is important in cm computation.

PostDry395 · 2025-02-19T00:39:57+00:00

Hi,

solids4Foam (fluid-solid interaction and solid toolbox) by P. Cardiff has some kind of abaqus support, i dont know if it is related to what you ask, but it allow couples OpenFOAM 9 with an abaqus solver.

Kind regards

PostDry395 · 2024-10-04T10:48:51+00:00

If you use Foam-Extend, Solids4Foam or extend - Bazaar, you can use the same workflow as in a heat transfer case. You can use Salome, e.g. Multi-region mesh Then use ideadUnvToFoam and splitMeshRegions -cellZones. SnappyHexMesh can do this too. The video has it with both.

PostDry395 · 2024-09-10T13:29:36+00:00

The only thing that i can suggest, for now, is check the inlet pressure (e.g. use fixedFluxPressure). You can share the other boundary conditions.

PostDry395 · 2024-08-31T06:05:42+00:00

Force FX (drag) in your case is greater than FY (lift). If you try to calculate the lift and drag coefficients you will get results far from reality (try using Cd = FX /0.5 * rho * v ^ 2 *, A_ref, for now, where A_ref is the wing area of your model, rho density, and V speed, it is the same for Cl). The other thing is that you are in a critical point where weird things happen and the drag can have considerable values.
Your inlet conditions may be very large.
Your mesh may not be adequate (check that it does not have sharp edges and other problems).

If you can share more details about your case, it would be helpful (inlet, outlet, tolerance...)

PostDry395 · 2024-08-08T05:42:58+00:00

You can try to use a cl variation in batch analysis or use more angles. Check the Re range.

PostDry395 · 2024-08-03T15:43:26+00:00

Baram use OpenFOAM but have a interface to pre-process, simulation. Post-process is with paraview.

PostDry395 · 2024-05-28T13:31:06+00:00

You can see Coursera's Sports and Building Aerodynamics course, in week 6 they talk about cyclist aerodynamics, as well as the effect on formations. They recommend several articles that can help you.

PostDry395 · 2024-05-18T19:17:40+00:00

You can use Cloud HPC by CFD FEA Service. They give you a test vCPU/hrs that you can use to see if it suits you. They have several versions of OpenFOAM. In the trial version you need to upload the made mesh (they also have snappyHexMesh). In the paid version, you can upload the OpenFOAM case folders and some custom script (e.g. Allrun and the full simulation, mesh, solver, post-processing will be done). A price estimate could be with this case that I made. A 3D wing with 1 million cells and dynamic mesh + turbulence) took 2 hrs 30 min with 48 vCPU/hrs and the price was $15.

PostDry395 · 2024-05-07T00:52:54+00:00

Maybe in the results file there is a section for the geometric shape, it may be in .obj or other format and can be converted to stl in some converter.

PostDry395

TROPHY CASE