Mitigating unsteady loads at low Reynolds numbers using a passive trailing-edge flap -- Supplementary material

This dataset contains videos showing the time evolution of the instantaneous vorticity field around the airfoil, for a number of selected cases. Each case is characterized by the length of the flap (a), the frequency of the heaving motion of the airfoil (f), the heaving amplitude (h), the density of the flap (rho_s) and the mean geometric angle of attack of the airfoil (alpha). Variables are normalized with the free-stream velocity (U_inf), the airfoil chord (c), and the fluid density (rho).

Case A1 corresponds to alpha=5º, rho_s/rho = 1.5, pi*f*c/U_inf = 0.3, h/c = 0.15. Values of a/c = [0, 0.25, 0.375, 0.5, 0.75] are considered. Case A2 corresponds to alpha=5º, rho_s/rho = 1.5, pi*f*c/U_inf = 0.3, h/c = 0.25.

Values of a/c = [0, 0.25, 0.375, 0.5, 0.75] are considered. Case A3 corresponds to alpha=5º, rho_s/rho = 1.5, pi*f*c/U_inf = 0.3, h/c = 0.50. Values of a/c = [0, 0.25, 0.375, 0.5, 0.75] are considered.

Case B3 corresponds to alpha=5º, rho_s/rho = 1.5, pi*f*c/U_inf = 0.5, h/c = 0.50. Values of a/c = [0, 0.25, 0.375, 0.5, 0.75] are considered.