Airfoil Not Showing Up In ParaView

ae.r.ospace00 · February 1, 2024, 19:44

I'm trying to use OpenFOAM to find the lift, drag, etc. on an airfoil/wing section I have. If I'm using the 3D wing section, I do have an .stl file. If it's the airfoil, I have a set of x, y coordinates outlining the airfoil in a .dat file. I am trying to edit a tutorial that came with OpenFOAM to change out my .stl file currently. I've made adjustments in blockMeshDict and snappyHexMeshDict to replace the files and measurements used in the motorbike tutorial.

The problem I'm having is that the case runs without errors and allows me to send it to ParaView, but it's an empty box. The walls of the space show up and have pressure values, but the wing section itself isn't appearing inside. I'm also getting all zeros for lift, drag, etc. What could I be doing wrong?

AtoHM · February 2, 2024, 02:35

Your meshing failed. Do not perform a simulation unless you have checked your mesh first.

Without further information my best guess is that you introduced a syntax or other error in snappyHexMesh which caused it to fail. The blockMesh was created successfully, otherwise you would not have a mesh to run on. Obviously your drag etc. is zero with no obstacle for the flow. You can share more information here: https://www.cfd-online.com/Forums/openfoam-meshing/ (or maybe this thread gets moved there altoghether by an admin).

February 1, 2024, 19:44	Airfoil Not Showing Up In ParaView	#1
ae.r.ospace00 New Member Join Date: Feb 2024 Posts: 1 Rep Power: 0	I'm trying to use OpenFOAM to find the lift, drag, etc. on an airfoil/wing section I have. If I'm using the 3D wing section, I do have an .stl file. If it's the airfoil, I have a set of x, y coordinates outlining the airfoil in a .dat file. I am trying to edit a tutorial that came with OpenFOAM to change out my .stl file currently. I've made adjustments in blockMeshDict and snappyHexMeshDict to replace the files and measurements used in the motorbike tutorial. The problem I'm having is that the case runs without errors and allows me to send it to ParaView, but it's an empty box. The walls of the space show up and have pressure values, but the wing section itself isn't appearing inside. I'm also getting all zeros for lift, drag, etc. What could I be doing wrong?

Similar Threads
Thread	Thread Starter	Forum	Replies	Last Post
Problem with airfoil shape optimization	robyTKD	SU2 Shape Design	7	March 7, 2022 17:18
Airfoil with simpleFoam and kOmegaSST: high drag values?	Tsiolkovsky	OpenFOAM Running, Solving & CFD	6	November 21, 2018 06:56
2D FFD Optimization	RLangtry	SU2	2	August 5, 2014 10:48
Problem with restart solution in shape_optimization.py	robyTKD	SU2 Shape Design	21	May 29, 2013 10:26
Airfoil boundary condition	Frank	Main CFD Forum	1	April 21, 2008 19:36

February 2, 2024, 02:35		#2
AtoHM Senior Member M Join Date: Dec 2017 Posts: 703 Rep Power: 13	Your meshing failed. Do not perform a simulation unless you have checked your mesh first. Without further information my best guess is that you introduced a syntax or other error in snappyHexMesh which caused it to fail. The blockMesh was created successfully, otherwise you would not have a mesh to run on. Obviously your drag etc. is zero with no obstacle for the flow. You can share more information here: https://www.cfd-online.com/Forums/openfoam-meshing/ (or maybe this thread gets moved there altoghether by an admin).