Convergence error on static structural analysis of wing assembly
Hi all, I am trying to perform static structural analysis of an assembled wing under certain speed. I ran a CFX fluent to obtain the pressure distribution on the wing and transfer it to the static structural which I need to obtain the performance of the assembled structure. But it seems like the solver couldn't converge and I'm lost. I don't know what I did wrong and don't really know where to look for solution. The whole idea is to perform topology optimization on the wing rib but now I couldn't obtain the performance of the un-optimized structure.
Really appreciate if someone can point me a direction on what I did wrong.
PS: I couldn't upload the wbpz file so I shared the google drive link. The file name is student community.wbpz