Author(s)

K.A. Belibassakis, O.K. Politis & M.S.Triantafyllou

Abstract

A 3-D unsteady vortex lattice technique is applied to the analysis of a pair of vertical oscillating wing tails, in order to investigate quantitatively its propulsive performance. Each lifting component undergoes a combined transverse and angular motion at the same frequency, in a uniform inflow condition A free- wake analysis is incorporated in order to account for the effects of non-linearity, especially at increased amplitudes of oscillatory motion Wing thickness effects are taken into account by an appropriate linearisation of the no-entrance boundary condition, and the effects of viscosity by means of a factional drag coefficient applied to the solid surface. Numerical results are presented vs. experimental me

Keywords