Abstract
Based on blade element/momentum theory the aerodynamic impact on rotor controls and blade flapping caused by a straight line vortex penetrating orthogonally the plane of a rotor disk is solved using a realistic swirl velocity profile. The collective and cyclic controls needed for disturbance rejection and the coning and cyclic flapping motion developing are computed.
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Schedule a callMore From: Journal of the American Helicopter Society. American Helicopter Society
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