FLIP TIP ROTOR BLADES

Valana Wells (Inventor)

Research output: Patent

Abstract

The "flip-tip" rotor blade is intended to alleviate the noise and other detrimental effects associated with the interaction of a helicopter (or other) rotor blade with its vortex wake. The concept is applicable to the blades of rotors or propellers which operate under conditions which are conducive to the production of blade-vortex interactions (BVI). Examples of vehicles which may operate under these conditions include helicopters of all varieties, tilt-rotor aircraft, tilt-wing aircraft, rotor/wing aircraft, stowed-rotor aircraft, autogyros, and any other aircraft types with a vertical or close to vertical descent capability and for which the lift in descent is provided by a vertical-axis rotor or propeller.
Original languageEnglish (US)
StatePublished - Jan 1 1900

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