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.
Claims5
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 first neutral position, and the second position generating a shock wave proximate to a leading edge of the airfoil, the airfoil further comprising a trailing edge selectively moveable between a second neutral position and a lowered position, the method comprising the steps of:
- maintaining the airfoil in the first position when the speed is less than a first limit, the first limit being a subsonic speed greater than Mach 0.70 or a transonic speed;
- and
- moving the airfoil to the second position when the speed is greater than a first limit, wherein the leading edge is in a raised position and the trailing edge in the lowered position when the airfoil is in the second position,
- wherein the shock wave is formed at a localized concave discontinuity on a forward portion of an upper surface of the airfoil.
Dependencies are inferred from the claim text.