Main rotor-body action for virtual blades model
Kazan National Research Technical University n.a. A. N. Tupolev (KNRTU-KAI), Kazan, Russia
7 University of Glasgow, Glasgow, UK
Corresponding author: firstname.lastname@example.org
Published online: 4 June 2018
This research aims to investigate a virtual blade model and assess rotor influence on helicopter fuselage aerodynamics. The rotor disk is discretized in the azimuthal direction, and a time-varied pressure jump is applied in regions occupied by the blades. To obtain the pressure jump, an actuator disk is employed using uniform and non-uniform blade load distribution, based on momentum theory.
© The Authors, published by EDP Sciences, 2018
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