Aeroelasticity of supersonic ONERA M6 wing; parametric studies using a fully-coupled computational approach

The aeroelastic phenomena of a modified ONERA M6 wing equipped with wingtip devices in transonic 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 winglet 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.