3d flutter
 

hello everyone first of all i am a fresher trying to simulate flutter in 3d case of a wing .i have successfully done the flutter case for 2d using the inbuilt programme in su2_aero-elasticity.i want to know is it possible to built a coupled model of cfd and fem in the su2 model using a single configuration file.can i built the solid model and solve it using the fem solver and input the output to the fem to cfd for mesh deformation and cfd analysis using the single cfg file for both .and can the interface be built using python code .kindly reply

Hi,
The most active group working in that area are

http://su2.stanford.edu/teams/IC_Team.html

or

http://qub.ac.uk/research-centres/ca...2MPCCINastran/

Maybe you can contact them,

Best regards,

Francisco Palacios
SU2 lead developer

fea solver
 

thank you .I have recently gone through the fea solver where i have few dobts as stated below.kindly guide me through

1 can a solution file of cfd be linked as input to fea solver is there any provision made for that and vice versa because that may help me in importing the pressure file onto the nodes of structure surface of wing and if so whats the format.how to link each data sol in unsteady case from cfd to fea

2.the fea solver is currently only providing von mises stress as output rather than displacements .is thier any way to get this displacements values as output

3 there is one bc_flow pressure boundary condition what does that stand for in fea solver and how does that work

kindly help me with answers if possible

Hi,

thanks for your interest. The FEA solver is currently under intense development and testing and thus has not been merged yet into the release version of the code. We expect to do it shortly, with brand new features. On its latest beta version the FEA solver generates both displacements and stress fields as outputs. The bc_flow pressure boundary condition is also currently being reformulated.

Best regards,
Ruben Sanchez

ok thanks a lot .expecting that there would be some options for 3d flutter analysis also .but all together the software is very good

i ran the beam problem for latest su2 3.2.7 .it seems like it doesnot provide displacement as output




TITLE = "Visualization of the surface solution"
VARIABLES = "x","y","Conservative_1","Conservative_2", "Von_Mises_Stress", "Flow_Pressure"
ZONE NODES= 436, ELEMENTS= 436, DATAPACKING=POINT, ZONETYPE=FELINESEG
0.000000e+00 -1.000000e-02 4.857543e-04 -1.277594e-02 1.003697e+06 0.000000e+00
1.758794e-03 -1.000000e-02 4.857510e-04 -1.269056e-02 9.932117e+05 0.000000e+00
3.517588e-03 -1.000000e-02 4.346568e-04 -1.277593e-02 1.011840e+06 0.000000e+00
5.276382e-03 -1.000000e-02 4.857477e-04 -1.260519e-02 1.003343e+06 0.000000e+00
8.793970e-03 -1.000000e-02 3.835593e-04 -1.277593e-02 1.020270e+06 0.000000e+00
1.055276e-02 -1.000000e-02 4.857441e-04 -1.251981e-02 1.045352e+06 0.000000e+00
1.582915e-02 -1.000000e-02 3.324621e-04 -1.277592e-02 1.012095e+06 0.000000e+00
1.758794e-02 -1.000000e-02 4.857397e-04 -1.243443e-02 1.127047e+06 0.000000e+00
2.462312e-02 -1.000000e-02 2.813652e-04 -1.277592e-02 9.821737e+05 0.000000e+00
2.638191e-02 -1.000000e-02 4.857339e-04 -1.234905e-02 1.257821e+06 0.000000e+00
3.517588e-02 -1.000000e-02 2.302688e-04 -1.277592e-02 9.304990e+05 0.000000e+00
3.693467e-02 -1.000000e-02 4.857263e-04 -1.226367e-02 1.444182e+06 0.000000e+00
4.748744e-02 -1.000000e-02 1.791727e-04 -1.277591e-02 8.594749e+05 0.000000e+00
4.924623e-02 -1.000000e-02 4.857166e-04 -1.217828e-02 1.688509e+06 0.000000e+00
6.155779e-02 -1.000000e-02 1.280770e-04 -1.277591e-02 7.727136e+05 0.000000e+00
6.331658e-02 -1.000000e-02 4.857042e-04 -1.209290e-02 1.990227e+06 0.000000e+00
7.738693e-02 -1.000000e-02 7.698149e-05 -1.277590e-02 6.744497e+05 0.000000e+00
7.914573e-02 -1.000000e-02 4.856890e-04 -1.200752e-02 2.347512e+06 0.000000e+00
9.497487e-02 -1.000000e-02 2.588617e-05 -1.277590e-02 5.692429e+05 0.000000e+00
9.673367e-02 -1.000000e-02 4.856704e-04 -1.192214e-02 2.758377e+06 0.000000e+00
1.143216e-01 -1.000000e-02 -2.520909e-05 -1.277590e-02 4.618148e+05 0.000000e+00
1.160804e-01 -1.000000e-02 4.856481e-04 -1.183676e-02 3.221110e+06 0.000000e+00
1.354271e-01 -1.000000e-02 -7.630441e-05 -1.277590e-02 3.569483e+05 0.000000e+00
1.371859e-01 -1.000000e-02 4.856217e-04 -1.175138e-02 3.734370e+06 0.000000e+00
1.582915e-01 -1.000000e-02 -1.273999e-04 -1.277590e-02 2.594146e+05 0.000000e+00