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- W2418567316 abstract "The main objective of this paper is to describe the key physical features for modelling the unsteady aerodynamic effects found on helicopter rotor blade operating under nominally attached flow conditions away from stall. The unsteady effects were considered as phase differences between the forcing function and the aerodynamic response, being functions of the reduced frequency, the Mach number and the mode forcing. For a helicopter rotor, the reduced frequency at any blade element can’t be exactly calculated but a first order approximation for the reduced frequency gives useful information about the degree of unsteadiness. The sources of unsteady effects were decomposed into perturbations to the local angle of attack and velocity field. The numerical calculus and graphics were made in FLUENT and MAPLE soft environments. This mathematical model is applicable for aerodynamic design of wind turbine rotor blades, hybrid energy systems optimization and aeroelastic analysis." @default.
- W2418567316 created "2016-06-24" @default.
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- W2418567316 date "2016-01-01" @default.
- W2418567316 modified "2023-09-25" @default.
- W2418567316 title "Lift capability prediction for helicopter rotor blade-numerical evaluation" @default.
- W2418567316 cites W2142560920 @default.
- W2418567316 doi "https://doi.org/10.1063/1.4952208" @default.
- W2418567316 hasPublicationYear "2016" @default.
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