Identifying the location in space and time of a vortex breakdown over a wing is a key process that will provide valuable information to the aerodynamicists when designing aircraft wings. The breakdown of a vortex near the wing of an aircraft determines variations in the wing surface pressure and shear stress and affects the overall values of lift and drag. The recourse to Reduced Basis Methods will allow for a fast yet accurate prediction of the vortex breakdown location as well as will allow obtaining significant information about the pressure and shear stress fields over the wing in correspondence of the breakdown region. Key objectives:

Perform an unsteady CFD simulation (https://su2code.github.io) of the flow over a delta wing capable to develop a vortical structure from the leading edges that eventually will break down; Use Reduced Basis Methods to identify the instant of time when the vortex will break down and provide a detailed description of the flow field; Validate the prediction obtained by measn of Reduced Basis methods via high fidelity CFD simulations.