A direct panel method based on a novel boundary integral formulation for the velocity potential is presented and to helicopter rotors experiencing bladevortex interaction. It avoids the numerical instabilities arising in the standard direct panel method in case of blade/wake impingement. This aerodynamic formulation yields a unified approach for the calculation of free-wake evolution and the blade-pressure field; it is fully 3-D, includes body-thickness effects, and can be applied to blades with arbitrary shape and motion. Blade-pressure predictions and the acoustic fields correlate well with wind-tunnel test data for helicopter rotors in descent flight, in which severe bladevortex interaction occurs.
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Gennaretti et al. (2007) studied this question.
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