[nauman55]

hi need help in meshing of an aircraft wing attached as picture.
regards

[Far]

If you follow the wing body tutorial and some techniques to mesh the region inside the tip (a thread started by cfd-seeker and some other threads), you should be able to get a decent mesh.

If you want us to try, then share the files.

[nauman55]

Far sir i have tried that wing body tutorial and changed my blocking strategy but the pre mesh i got had negtive volumes and uncovered faces. sir may i know in which format i shud upload the geomerty? ansys or the parasolid file?
regards

[mraxx]

I have a similar problem. I spent hours on trying to mesh this geometry and almost threw my computer out of the window. The attached picture shows a medley of some of the worst outcomes of my attempts

Far, since you offered your help to naumann55, maybe you can have a look at my ICEM project and see if you can fix it. I do not really care about perfect mesh quality. Your help is greatly appreciated!
Here is the ICEM project file: http://www.file-upload.net/download-...irbus.zip.html


Also, I have some questions... maybe answers to this questions would bring me closer to generating the mesh by myself.

1. The ragged trailing edge shown in the picture below can be fixed by lowering the edge criterion, right? Because this did not seem to work for me but maybe I did not go low enough.

2. Many times, ICEM did not only mesh the FLUID domain but simply meshed through the surfaces. What am I doing wrong? What I did is I created a FLUD body and a SOLID body in the aircraft. When computing the mesh, I turned of the SOLID and selected Input Geometry: Visible.

3. Why are there almost never prisms on the surfaces although i specify prisms in the part mesh setup, in the prism meshign setup and check "create prism layers" in the computer volume mesh section?

4. I created a surface through the body of the aircraft as symmetry plane. ICEM created a surface mesh on this plane. But this surface mesh is also on the part of the surface that lies inside of the aircraft body. I would expect that to be a problem for the solver. Do I need to cut the inside of the aircraft out of the symmetry surface?

Thanks in advance for your answers!

[Far]

wow classic. I will try on model as I have never seen such a Beauty in my life. Awesome


All day, every day

[nauman55]

sir sent you the geometry file on your email. request acknowledge reciept.
regards

[Far]

There were many problems in geometry including outer surfaces, wing and fuselage. Corrected them but the fuselage surface cannot be rebuilt in ICEM and it must be corrected in your CAD software or design modeller.

[Far]

[nauman55]

thanx alot sir i will do that. i request if you can email me the blocking and mesh you have created. get back to you after repairing the highlighted area.
regards

[Far]

same blocking can be reused. Similar approach is used as used in Simon's three part tutorial on airfoil meshing.

Can you think of any other topology? like wing body tutorial? what do you think which one will be better?

[Far]

Look at the pictures. I have used edit edge > Automatic linear and you can notice there is unexpected deflection of one edge in lower portion of fuselage.

[Far]

Problem solved by dividing fuselage into two parts spanwise. Sending you files... And same blocking was re-used...

Quality > 0.61 and min angle > 18

Procedure to divide fuselage into two surfaces:

1. create iso-curve at 0.5 location on both sides (pressure and suction)
2. Segment surface by created curves.
3. update association and also make some manual association at newly created air-foil (edge to curve and vertex to point)







Enjoy at RCMS with KP...

[Far]

@Max:

I took a look at your problem and I found it interesting. I remember similar problem at AIAA drag prediction workshop and meshing was done in ICEM hexa and tetra.

I can try to reproduce both hexa and tetra meshing if you are interested...

[Far]

No problem in Fluent. Please turn of "solid" when you are generating unstructured mesh.

[nauman55]

sir it is still not readable by fluent. the error message says of some missing faces. may be i have messed up with the boundary conidtions.
regards

[Far]

As you can see in above pic, mesh has no problems in fluent.

[cfd seeker]

Enjoy at RCMS with KP...

Hilarious

[mraxx]

Originally Posted by Far

@Max:

I took a look at your problem and I found it interesting. I remember similar problem at AIAA drag prediction workshop and meshing was done in ICEM hexa and tetra.

I can try to reproduce both hexa and tetra meshing if you are interested...

Yes, I am more than interested!

[raj.singh]

is O Grid possible for such blocking???

[cesarcg]

Dear mraxx,

I took a look at your geometry and saw that some surfaces at the tail of the fuselage were not cut, and thus these are outside of the fluid domain. The command "split surface by plane might be applied". I also saw that you model have many details at the inlet of the engine that can be omitted in a first approach.

Moreover, in my experience I think that the hardest part of the meshing will be at the regions where the wing, and stabilizers (vertical and horizontal) join the fuselage; as well as where the engine joins the wing. It is probably better to use tetra/prism in such regions as suggested by @Far.

@Max:

I took a look at your problem and I found it interesting. I remember similar problem at AIAA drag prediction workshop and meshing was done in ICEM hexa and tetra.

I can try to reproduce both hexa and tetra meshing if you are interested...

I'll try to help during my free time.

Regards,
César