[hgh]

Originally Posted by Shakeel

I have taken a different route to setting up the problem. I have already created a CFD model for the aerofoil using ICEM CFD and have solved it for steady state using CFX. I then wanted to use this CFD model as this will make my work later on in the project a whole load easier. I linked the CFD model with a structural model in ansys workbench (as mentioned by Daniel in the post above, this has limited my options in terms of the meshing but I have done all the meshing) and have set-up all the coupling parameters using CFX-pre. I have also tried to import a structural model but I cannot seem to import an Ansys db file.

The aerofoil is not of standard design so it is difficult to make without a proper CAD software, I was trying to simulate a 2D aerofoil, as I mentioned before I have tried:

1) Solid aerofoil closed section, solves and converges

2) Surfaces over leading and trailing edge solid wing box, works but doesn't converge

3) Surfaces over all the aerofoil open sides, doesn't work at all.

4) I have even tried modelling the thickness and using volume mesh.

Daniel, thank you for your advise, I have found the .out file for the structural model, I also found the following errors:

SURFACE INTERPOLATION MAPPING

PROFILE PRESERVING INTERPOLATION MAPPING
--------------------------------------------------------------------
Sending region name = 1
From sending process = ANSYS
to receiving process = CFX
Transferring variable = DISP

*** ERROR *** CP = 9.922 TIME= 11:58:27
Error in bucket search algorithm for load surface mapping.
Processing complete
--------------------------------------------------------------------


CONSERVATIVE INTERPOLATION MAPPING
--------------------------------------------------------------------
Sending region name = wing
From sending process = CFX
to receiving process = ANSYS
Transferring variable = Total Force
Sending Side: Total Area = 8.16997E+00
Non-Matching Area Fraction = 99.5478%
No. of Un-Mapped Nodes = 784
Receiving Side: Total Area = 2.04224E+00
Non-Matching Area Fraction = 98.2565%
No. of Un-Mapped Nodes = 14882

*** WARNING *** CP = 11.466 TIME= 11:58:29
The component MFLC_1_2_FORC_1 was created for MFLC,1,2,FORC,1 command
to display improperly mapped nodes. Set /debug,,2 for more
information on improperly mapped nodes.

Processing complete
--------------------------------------------------------------------


*** ERROR *** CP = 11.466 TIME= 11:58:29
Error during setup - Skipping the remaining MultiField analysis.

*** ERROR *** CP = 11.466 TIME= 11:58:29
Error during setup - Skipping the remaining MultiField analysis.


NUMBER OF WARNING MESSAGES ENCOUNTERED= 2
NUMBER OF ERROR MESSAGES ENCOUNTERED= 3

This definitely looks like a coupling error with the structural model, but I am not sure how else to model this case. Any suggestions from the either of you? I have attached a few images to show the progression I spoke of above.

Thank you all for your continued assistance,
regards

Shakeel

Hello
For rigid airfoil aeroelastic analysis, I do not know what to do to airfoil to move up and down (in terms of time step)?
How do I give the time step?


Thank

[hgh]

Originally Posted by Pocket

Alternatively, if you don't have to fiddle around in the .inp file directly, you can use Workbench and link the structural setup cell to the cfx setup cell.
Then the program directly links your two simulations and creates and links the .inp file directly.


@Shakeel
Your error looks like the mechanical solution encountered a problem.
Look at the ANSYS output file (you can see it in the cfx solver manager) and search for an error in there.


cheers
Daniel

Hello
For rigid airfoil aeroelastic analysis, I do not know what to do to airfoil to move up and down (in terms of time step)?
How do I give the time step?


Thank