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Abstract
A simple analytical real-time capable model to account for fuselage-induced velocities at rotor blade elements is described at the example of the Bo105 fuselage. Data of the fuselage-induced flow fields in the volume of rotor operation above the fuselage are first computed by a panel method in the range of angle of attack and sideslip of [Formula: see text]. The model parameters are then estimated based on these data. The usefulness of the model in combinations of angle of attack and sideslip is demonstrated.
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