I am trying to analyze a lofted airfoil with a spar inside of it. However I'm getting unusually low FOS around the bolt holes even when I add upwards of 10 plies. (Each ply being 0.3mm thick). I've used bonded condition on the spar faces to mimic an adhesive. The contact tool shows that all contacts are closed so that should be fine.
I was getting a pivot error earlier but I turned off the setting in analysis settings but I feel like that has something to do with it I just didn't know how to solve it.
I'm constraining the model in 4 locations with remote displacement setting all the translations to 0 and the rotations to free. The bolt holes go through the spar and airfoil so I'm using 1 remote displacement for both the spar and airfoil (doing this 4 times so one per bolt hole). I'm applying a -1334N force. I applied 10 plies on the spar and 2 plies on the airfoil so I feel like I should be getting FOS well above 1. So I'm wondering if anyone encountered this type of issue before and how they solved it.
Just for info: the spar and airfoil are two seperate thin bodies (shell method meshing). I am using the Puck failure criteria and turned on maximum stress and strain in the composite failure tool.
