METHOD AND APPARATUS TO IMPROVE LIFT TO DRAG RATIO OF A ROTOR BLADE

METHOD AND APPARATUS TO IMPROVE LIFT TO DRAG RATIO OF A ROTOR BLADE

In a first aspect, there is a method for improving a lift to drag ratio of a rotor blade (106, 70, 78), including providing a blade member (108) having a leading edge (114) and a trailing edge (116); providing a leading edge extension member (130); and coupling the leading edge extension member (130...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: FOSKEY, Christopher E, LANIGAN, Brendan P
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
AEROPLANES
AIRCRAFT
AVIATION
BLASTING
COSMONAUTICS
HEATING
HELICOPTERS
LIGHTING
MACHINES OR ENGINES FOR LIQUIDS
MECHANICAL ENGINEERING
OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
PERFORMING OPERATIONS
PRODUCING MECHANICAL POWER
TRANSPORTING
WEAPONS
WIND MOTORS
WIND, SPRING WEIGHT AND MISCELLANEOUS MOTORS
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Beschreibung
Zusammenfassung:In a first aspect, there is a method for improving a lift to drag ratio of a rotor blade (106, 70, 78), including providing a blade member (108) having a leading edge (114) and a trailing edge (116); providing a leading edge extension member (130); and coupling the leading edge extension member (130) to a portion of the leading edge (114) of the blade member (108) to form the rotor blade (106, 70, 78). In a second aspect, there is a rotor blade (106, 70, 78) including a blade member (108) having a leading edge (114), and a trailing edge (116); and a leading edge extension member (130) disposed on the leading edge (116) of the blade member (108), wherein the leading edge extension member (114) is configured to extend the chord length of at least a portion of the rotor blade (106, 70, 78). In a third aspect, there is a leading edge extension member (108) for a rotor blade (106, 70, 78) including a convex exterior surface (130e) configured to extend at least a portion of the chord length (C1) of the rotor blade (106, 70, 78).