Dynamic aeroelastic instabilities of fixed-wing aircraft in transonic and supersonic flows using a fully-coupled model

The aeroelastic phenomena of ONERA M6 wing in transonic and supersonic flight regimes is computationally studied using a fully-coupled aeroelastic approach. The present research concerns the development of a computationally efficient and accurate method for the aeroelastic studies of fixed wing in transonic and supersonic flows. Therefore, we propose a fully-coupled, time-marching aeroelastic approach utilizing an URANS model. The computational studies are carried out to assess the effect of the freestream Mach number and angle of attack on the structural dynamics and stresses developed in the ONERA M6 wing. The studies are carried out for a range of Mach numbers, M_∞ = 0. 8 – 1. 4, and angles of attack, α = {2°, 4°, 6°}. The analysis reveals that the aeroelastic deformation of the wing and induced stress in the wing structure increase with the freestream Mach number.