Resolvent analysis of a finite wing in transonic flow

Shock waves interacting with turbulent boundary layers on wings can result first in self-sustained flow unsteadiness and eventually structural vibration. Due to its importance modern wing design aircraft certification, the transonic physics continue be investigated intensively. Herein we focus discussion three main aspects. First, assess a practical implementation of an iterative resolvent algorithm linear harmonic incarnation industrial computational fluid dynamics code for computing optimal forcing response modes. This heavily relies efficient solution large sparse systems equations. Second, showcase application as predictive tool detect buffet unsteadiness, well before global stability analysis identify through weakly damped eigenmodes, using NASA common research model at wind-tunnel conditions. Third, discuss ability uncover modal physics, not identifiable analysis, revealing higher-frequency wake wingtip vortex modes while shedding some light elusive finite equivalent aerofoil mode. We demonstrate that earlier limitations when solving truncated singular value decomposition matrix-forming methods direct matrix factorisation, have been overcome ready use.