Abstract
A direct panel method based on a novel boundary integral formulation for the velocity potential is presented and applied to helicopter rotors experiencing blade-vortex interaction (BVI). It avoids the numerical instabilities arising in the standard direct panel method in case of blade/wake impingement. This aerodynamic solver yields a unified approach for the calculation of free-wake evolution and blade pressure field. It is fully 3D, includes body thickness eects, and can be applied to blades with arbitrary shape and motion. Blade pressure predictions and the corresponding acoustic fields correlate well with wind tunnel test data for helicopter rotors in descent flight, where severe BVI occurs.
Published Version
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