Using numerical methods, the aeroacoustic field induced by the interaction of a 4-bladed NASA SR-2 propeller and its wake with a wing is investigated under cruise conditions (Mach 0.6). The SmartRotor code, a coupled vortex particle and panel method, which is integrated with an acoustic solver based on the Farassat 1A formulation of the Ffowcs-Williams Hawkings equation, was used. Three main areas were investigated: the effect of propeller tip geometry on the propeller's wake and blade tip vortex; the effect of integrating a wing in the tractor configuration, including the effect of its position, and wing local leading edge sweep; and the effect of operating the combined wing/propeller system in off-design conditions such as low forward speed or in non-axial inflow.It was discovered that tip sweep is effective at reducing propeller tip vortex strength with no adverse effect on noise. Modifying tip dihedral was found to always increase tip vortex strength. Integrating a wing in the wake of the propeller increased the broadband noise generated, but had little effect on harmonic noise. The downstream position of the wing was found to not affect noise while vertical offset from the propeller axis increased noise. The most important discovery was that applying local leading edge sweep to the wing in the region of the propeller's wake decreases noise proportionally to the change in the angle between the helical tip vortex and the wing's leading edge. These noise reductions were on the order of up to 1.3 dB for overall sound pressure level, and 7.5 dB at the blade passage frequency.iii Acknowledgements First on the list of many people to thank must be my supervisor, Professor Daniel Feszty. His constant enthusiasm and support of my work was invaluable whenever simulations weren't working or results seemed less than reasonable. At the same time, his way of providing guidance while allowing me to choose the direction of my research allowed me to follow up on interesting results and truly take ownership of this work. For this and so much more, thank you.

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