Hi,
I am trying to perform buckling analysis of aircraft wing in MSC Nastran which is modelled in Patran. The wing consists of ribs, skin and spars. I divided lift load by planform area and applied on the wing upper surface as uniform pressure. The Root section nodes are fixed. While performing...
Hi,
I am trying to perform buckling analysis of aircraft wing in MSC Nastran which is modelled in Patran. The wing consists of ribs, skin and spars. I divided lift load by planform area and applied on the wing upper surface as uniform pressure. The Root section nodes are fixed. While performing...