Abstract “Store Separation: Theoretical Investigation of Wing Aeroelastic Response”
The objective of this paper is to propose a novel approach to the study of the steady and unsteady aeroelastic behavior of a wing during the flight, as for example in cases where there is a release of underwing bodies in military aircrafts.
This new methodology is based on a structural modal superposition approach and a mesh morpher fully integrated in the fluid dynamic (CFD) solver, that allows to greatly reduce the analysis time of the classic approach to a FSI problem, typically characterized by an exchange of data between the structural and the fluid dynamic solver.
The following describes the whole procedure developed and the main obtained results.