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- W2069480445 abstract "This paper presents a new treatment of the aeroelastic scaling problem for rotary wing vehicles (i.e. helicopters and tiltrotors). It is shown that the offset hinged spring restrained blade model is the rotary wing equivalent of the typical cross-section that has been used during the last 50 years to obtain aeroelastic scaling laws for fixed wing vehicles. A new two-pronged approach for developing refined aeroelastic scaling laws for rotary-wing aeroelastic and aeroservoelastic applications is presented. It combines the classical approach with computer simulations to obtain new refined aeroelastic scaling relations. The rotary wing scaling laws are applied to the vibration reduction problem in helicopter rotors using an actively controlled, partial span, trailing edge flap. The results obtained for a Mach scaled rotor are compared with those obtained for a Proude scaled rotor. The results indicate that the Mach scaled rotor is needed so as to obtain the correct actuation requirements for vibration reduction." @default.
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- W2069480445 date "2004-06-01" @default.
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- W2069480445 title "Aeroelastic scaling for rotary-wing aircraft with applications" @default.
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- W2069480445 doi "https://doi.org/10.1016/j.jfluidstructs.2004.03.003" @default.
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