Wing and method for reducing effects of propeller airflow on lift distribution
AssigneeAirbus Deutschland 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.
Claims9
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.
A method for reducing the induced drag that is increased as a result of at least one propeller slipstream flowing onto the 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.
Dependencies are inferred from the claim text.