A rotor hub fairing system (36) for use in a counter-rotating, coaxial rotor system (12) is provided including an upper hub fairing (38) defined about an axis and a lower hub fairing (40) defined about the axis. A shaft fairing (42) is disposed between the upper hub fairing (38) and the lower hub fairing (40). The geometry of the shaft fairing (42) is configured to encourage a wake adjacent the upper hub fairing (38) to form collectively with a wake adjacent the lower hub fairing (40).
DRAG REDUCTION OF HIGH SPEED AIRCRAFT WITH A COAXIAL-ROTOR SYSTEM
WIDERSTANDSREDUZIERUNG EINES HOCHGESCHWINDIGKEITSFLUGZEUGS MIT EINEM KOAXIALROTORSYSTEM
RÉDUCTION DE LA TRAÎNÉE D'AVION À GRANDE VITESSE AVEC UN SYSTÈME DE ROTOR COAXIAL
2020-04-15
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Drag Characteristics and Reduction Test for Hub of Coaxial-rotor Helicopter
DOAJ | 2020
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