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Computational Tracing of BVI Phenomena on Helicopter Rotor Disk


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DOI: https://doi.org/10.15866/ireaco.v16i4.24442

Abstract


This paper presents a computational methodology for tracing the locations of Blade Vortex Interaction (BVI) phenomena on a helicopter rotor disk. This methodology utilizes Vortex Element Method for rotor free wake computations. Wake vortices are modeled by a series of discrete vortex elements and induced velocity on rotor disk is calculated for the distorted wake geometry, integrating Biot-Savart law in closed form over each one of them. Bound circulation variations and unsteady blade airloading as a result of the nonuniform induced downwash are computed by blade element method. Wake roll up process, vortex core modeling and elastic blade motion are some of the aerodynamic topics modeled with special care in the developed procedure. BVI locations are detected and the phenomena are categorized as parallel, perpendicular and oblique regarding their orientation relative to rotor blade. The corresponding intensity and locus for each category are calculated. By these means, specific BVI phenomena can be isolated and their influence on blade downwash and airloads distribution can be demonstrated. The computational results of BVIs effects on blade airloading are compared with experimental data. These data are derived from model-rotor wind tunnel tests, performed in the duration of joined European research programs.
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Keywords


Helicopters; Rotor Aerodynamics; Blade Vortex Interactions; Vortex Core

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References


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