Aerofoil blockMesh
Can anyone tell me how an ideal block topology of an aerofoil mesh looks like. There are various types of grids like O, C and H and I am struggling to get an good aerofoil mesh.
I had a go on the C mesh but i am getting a lot of non orthogonal faces combined with big skew number. Anyone any idea ? |
blockMesh geometry
Hi
I am trying to create an aerofoil mesh using blockMesh but I am getting bad distribution around my leading edge. I am struggling to get orthogonality on the leading edge....... Any ideas about how the geometry should look like? |
BlockMesh
Has anyone an idea how a blockmesh structure for an aerofoil looks like.......I tried different blocking strategies but I am getting high skew number.
I appreciate any suggestions. Thanks |
NonOrtho faces blockMesh
hi there
i want to know if in openfoam is possible to get rid of the nonorthogonal faces .... below i have my mesh which failed to checkMesh i'll appreciate your help Create time Create polyMesh for time = 0 Time = 0 Mesh stats points: 8250 internal points: 0 faces: 16028 internal faces: 7780 cells: 3968 boundary patches: 5 point zones: 0 face zones: 0 cell zones: 0 Overall number of cells of each type: hexahedra: 3968 prisms: 0 wedges: 0 pyramids: 0 tet wedges: 0 tetrahedra: 0 polyhedra: 0 Checking topology... Boundary definition OK. Cell to face addressing OK. Point usage OK. Upper triangular ordering OK. Face vertices OK. Number of regions: 1 (OK). Checking patch topology for multiply connected surfaces ... Patch Faces Points Surface topology inlet 32 66 ok (non-closed singly connected) outlet 124 250 ok (non-closed singly connected) topAndBottom 124 250 ok (non-closed singly connected) Airfoil 32 66 ok (non-closed singly connected) frontAndBack 7936 8250 ok (non-closed singly connected) Checking geometry... Overall domain bounding box (-10 -10.0078 0) (0.30998 0 0.1) Mesh (non-empty, non-wedge) directions (1 1 1) Mesh (non-empty) directions (1 1 1) Boundary openness (-7.55518e-19 8.54205e-19 -2.26297e-16) OK. Max cell openness = 2.19942e-16 OK. Max aspect ratio = 65.8488 OK. Minumum face area = 1.94491e-05. Maximum face area = 0.386396. Face area magnitudes OK. Min volume = 1.94491e-06. Max volume = 0.0386396. Total volume = 8.19545. Cell volumes OK. Mesh non-orthogonality Max: 73.7915 average: 7.97915 *Number of severely non-orthogonal faces: 3. Non-orthogonality check OK. <<Writing 3 non-orthogonal faces to set nonOrthoFaces Face pyramids OK. Max skewness = 2.56447 OK. Coupled point location match (average 0) OK. Mesh OK. End |
Greetings Andrei,
I'm a bit late on this, but I've merged your questions into a single thread. AFAIK, doing an aerofoil directly in blockMesh is a very complicated work of art! I'm not familiar with any tutorial that does this, but I do know the following:
Best regards, Bruno |
Hi Andrei, Hi Bruno,
Quote:
I managed to create a NACA0012 in blockMesh which was actually rather simple. Here is a link to a thread, which also contains the answer to your last question: - http://www.cfd-online.com/Forums/ope...-naca0012.html post #5 has an example blockMeshDict which gives you a basic idea. In a nut shell: - use c-type mesh - use any offset calculator which is around on the internet for calculating an offset of your airfoil - use polyLine in your blockMeshDict to introduce your foil into the mesh I hope I could contribute regards |
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1 Attachment(s)
This website provides a small Octave script that directly generates a blockMeshDict for a C-type mesh for any NACA airfoil:
https://www.hpc.ntnu.no/display/hpc/...l+Calculations I find it to be quite useful. I'll upload it here, in case the URL changes (GNU General Public License). |
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