Wing and method for reducing effects of propeller airflow on lift distribution
AssigneeAirbus Operations GmbH
InventorRoland Kelm
Life of this patent
Estimating the term…
Abstract
A wing for an aircraft includes a non-balanced lift gradient because as a result of at least one propeller slipstream flowing onto the wing the induced drag of the wing is increased. To reduce the increased induced drag, the wing comprises a first region with a reduced local wing camber and/or reduced local twist, and a second region with an increased local wing camber and/or increased local twist. The first region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move upwards. The second region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move downwards.
Claims12
A wing for an aircraft for reducing the induced drag that is increased as a result of at least one propeller slipstream flowing onto the wing, the wing comprising:
- a first region with at least one of a reduced local wing camber and reduced local twist, and a second region with at least one of an increased local wing camber and increased local twist,
- wherein the first region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move upwards, and
- wherein the second region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move downwards;
- in which the first region comprises a reduced local wing camber, and the second region comprises an increased local wing camber.
A method for reducing the induced drag that is increased as a result of at least one propeller slipstream flowing onto a wing, comprising:
- reducing the local lift coefficient of the wing in a first region by use of at least one of a reduced local wing camber and reduced local twist, and increasing the local lift coefficient in a second region by use of at least one of an increased local wing camber and increased local twist,
- wherein the first region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move upwards, and
- wherein the second region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move downwards.
An aircraft comprising a wing for reducing the induced drag that is increased as a result of at least one propeller slipstream flowing onto the wing, the wing comprising:
- a first region with at least one of a reduced local wing camber and reduced local twist, and a second region with at least one of an increased local wing camber and increased local twist,
- wherein the first region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move upwards, and
- wherein the second region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move downwards.
A wing for an aircraft for reducing the induced drag that is increased as a result of at least one propeller slipstream flowing onto the wing, the wing comprising:
- a first region with at least one of a reduced local wing camber and reduced local twist,
- a second region with at least one of an increased local wing camber and increased local twist,
- wherein the first region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move upwards, and
- wherein the second region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move downwards, and
- which wing comprises two adjacent trailing edge flaps on each side of the wing deflectable in opposite directions for providing the reduced local wing camber of the first region, and the increased local wing camber of the second region.
Dependencies are inferred from the claim text.