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Interface between CAPS and FUNtoFEM to automatically generate coupled structure and fluid meshes.
Keep getting panel buckling solutions, with OML panels near the root sometimes buckling. We are still experiencing panel buckling solutions even for reasonably large thicknesses near the root of the wing. Will try adding stringers and maybe also add a wing box so that the hard cantilever constraint is not applied at the root rib.
NacaWing
Producing high stresses in the trailing edge of the rib (due to the sharp corner present). @sean-engelstad tried chopping off the ends of the ribs in the .csm file, but then the structural mesh generation fails; tried unioning a wire object to close the edges on the surface of the OML.
nacaWing
Pointwise reports a segmentation fault but continues to run.
Plan is to run full aerothermoelastic forward analysis with funtofem and ESP/CAPS for diamond wing case. Flow will be laminar meaning viscous forces will be present. However, negative cell volumes appear within the first few iterations due to the fluid cells in the boundary layer being thin triangles. Need to work on improving either the geometry/stiffness settings or the fluid mesh aka pointwise settings for laminar case.
examples/diamondWing/
We're trying to run a structural optimization to minimize mass subject to stress constraints for the nacaWing in order to size the thicknesses of each shell. Several components of the dstress/dthickness gradient are very large while others are small. I am currently using PSQP algorithm from PyOptSparse. The optimization algorithm currently steps way too far in the design space, pushing many of the thicknesses to the minimum thickness. It might be because the optimization begins in the infeasible region due to high stresses. Maybe I should allow a large maximum stress originally.
NacaWing case
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