3-dimensional wing-vortex interaction are studied in the thesis, which occur in many flight conditions of Rotating wing, tilt rotor and vstol aircraft.
A 3-dimensional vortex flow is generated from a wing at angle of attack. A small thin wing is used here as the vortex generator and a large thick main wing is placed at the downstream of the vortex generator. The change of the pressure distribution on the main wing surface due to the vortex and the change of the vote trajectory due to the main wing is calculated by using boundary element method(BEM) so called panel method. The vortex, modeled as a vortex ring is shed from the vortex generator at each time step and the vortex is convected with the local velocity, therefore, the change of the tragectory of the vortex can taken into account.
It turns out that significant surface pressure variations are observed, when the vortex passes near the leading edge of the wing. However, the circulation is nearly constant as in the case of a fixed line vortex-wing interaction and a 2-D point vortex-airfoil interaction.