摘要
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±90°.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.
