Effect of spanwise distributed camber morphing on dynamic stall characteristics of a finite-span wing

This paper investigates the influence of the spanwise-distributed trailing edge camber morphing on the dynamic stall characteristics of a finite-span wing at Re = 2 × 10⁵. The mathematical model of the spanwise-distributed trailing-edge camber morphing is established based on Chebyshev polynomials, and the deformed wing surface is modeled by a spline surface according to rib's morphing in the chordwise direction. The computational fluid dynamics method is adopted to obtain flow-field results and aerodynamic forces. The shear-stress transportv-γ model is introduced and the overset mesh technique is adopted. The numerical results show that the spanwise distributed trailing edge morphing obviously changes the aerodynamic and energy transfer characteristics of the dynamic stall. Especially when the phase difference between the trailing edge motion and the wing pitch is −π/2, the interaction between the three-dimensional leading-edge vortex and trailing-edge vortex is strengthened, and the work done by the aerodynamic force turns negative. This indicates that the trailing edge deformation has the potential to suppress the oscillation amplitude of stall flutter. We also found that as the trailing-edge camber morphing varies more complex along the spanwise, and the suppression effect decreases accordingly.