Variable wing leading edge camber
AssigneeBombardier Inc.
InventorPasquale Piperni
Life of this patent
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Abstract
A disclosed method reduces a wave drag on an airfoil traveling at a speed. At least a portion of the airfoil is configured to be selectively moveable between a first position and a second position. The first position is a neutral position, and the second position generates a shock wave near to the leading edge of the airfoil. The method includes the steps of maintaining the airfoil in the first position when the speed is less than a first limit and moving the airfoil to the second position when the speed is greater than a first limit.
Claims10
A method of reducing a wave drag on an airfoil traveling at a speed, at least a portion of the airfoil being configured to be selectively moveable between a first position and a second position, the first position being a neutral position, and the second position generating a shock wave proximate to a leading edge of the airfoil, the method comprising the steps of:
- maintaining the airfoil in the first position when the speed is less than a first limit;
- and
- moving the airfoil to the second position when the speed is greater than a first limit.
A method of reducing a wave drag on a wing of an aircraft traveling at a speed, at least a portion of the wing being an airfoil with a variable camber leading edge selectively moveable between a neutral position, an up-droop position, and down-droop position, the method comprising the steps of:
- moving the leading edge to the up-droop position when the speed is greater than a first limit, wherein moving the leading edge to the up-droop position generates a shock wave proximate to the leading edge to reduce the wave drag;
- and
- maintaining the leading edge in a neutral position when the speed is less than the first limit and greater than a second limit.
Dependencies are inferred from the claim text.