Rotorcraft Hub Drag Reduction

Summary: Rotor hub drag currently accounts for approximately 30-40% of the drag experienced by a helicopter in high speed forward flight. This project seeks to reduce hub drag by testing the effect of active flow control on the performance of hub and shaft fairings in order to reduce helicopter parasite drag for application to Future Vertical Lift. The active flow control fairing interfaces with the Army Rotor Wing Test Stand and the Penn State generic rotor hub for testing in the Army 7x10 foot wind tunnel at Ames Research Center, Moffett Field, CA.

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