This configuration of the modified ONERA M6 wing uses a blended winglet to minimize induced drag. At higher Mach numbers, this causes additional longitudinal loading due to the shockwave colliding with the winglet surface.
Velocity vectors highlight the intersection of aeroelastic effects and flow turbulence. At the trailing edge, the flow detachment is seen to vary with the aeroelastic response of the structure.
This video shows the deformation and equivalent stress in the wing structure amidst transonic flutter. As the dynamic aeroelastic instability compounds upon itself, the intensity of the wing loading increases.
The interaction of transonic shocks on the upper surface of the wing and the viscous boundary layer are captured. Vortices and unsteady flow detachment are shown to begin at the shock line. The increasing structural deformation of the wing causes the severity of these effects to increase.
Negative regions in contours of wall shear in the streamwise direction indicate local flow reversal. The dynamic aeroelastic instability in the wing-fluid system exacerbates the flow separation.
A comparison of the dynamic pressure distributions calculated by an unsteady rigid analysis and a dynamic aeroelastic analysis using tight fluid-structure coupling.
