Devices and methods to improve wing aerodynamics at low airspeeds
Aircraft wings are provided with aerodynamic devices that improve the wing's low airspeed aerodynamics. In preferred embodiments, the aircraft wings include a slat operatively positioned at the wing's leading edge for movement between a retracted position for relatively high airspeed aircraft operations, and a deployed position for relatively low airspeed aircraft operations. An aerodynamic device is positionally fixed to the wing laterally adjacent the leading edge slat, the device having a forward end extending forwardly of the wing leading edge. The device is operable in response to movement of the slat into the deployed position thereof so as to improve the aerodynamics of the wing at low airspeed aircraft operations, but provides substantially no aerodynamic improvement when the slat is in the retracted position thereof during high airspeed aircraft operations.
1. An aircraft wing having leading and trailing edges comprising:
a slat operatively positioned at an outboard portion of the aircraft wing adjacent to an inboard portion of the aircraft wing, wherein the slat establishes a respective outboard leading edge portion of the aircraft leading edge adjacent to an inboard leading edge portion of the aircraft leading edge, and wherein the slat is moveable between a retracted position for relatively high airspeed aircraft operations wherein the inboard and outboard leading edge portions of the aircraft leading edge are aligned with one another, and a deployed position for relatively low airspeed aircraft operations wherein the outboard portion of the aircraft leading edge established by the slat is displaced forwardly of the inboard leading edge portion of the aircraft wing; and
an aerodynamic device positionally fixed to the inboard portion of the aircraft wing laterally adjacent an inboard edge of the slat at a location between the inboard and outboard portions of the aircraft wing, the aerodynamic device having a forward end extending forwardly of the aligned inboard and outboard leading edges of the inboard and outboard portions of the aircraft wing, respectively, when the slat is in the retracted position thereof, wherein
the aerodynamic device is operable in response to movement of the slat into the deployed position thereof so as to improve the aerodynamics of the wing at low airspeed aircraft operations, and providing substantially no aerodynamic improvement when the slat is in the retracted position thereof during high airspeed aircraft operations.
2. The aircraft wing as in claim 1 , wherein the device is positionally fixed to the wing between the inboard edge of the slat and a wing-fuselage fairing which establishes the inboard portion of the aircraft wing.
3. The aircraft wing as in claim 1 , wherein the device is a substantially planar structure having arcuately rounded upper and lower edges.
4. The aircraft wing as in claim 3 , wherein each of the upper and lower edges is arcuately rounded about a radius of curvature that is substantially the same.
5. The aircraft wing as in claim 3 , wherein each of the upper and lower edges is arcuately rounded about a radius of curvature that is different.
6. The aircraft wing as in claim 5 , wherein the bottom edge of the device is curbed about a radius of curvature which is greater as compared to the radius of curvature of the upper edge.
7. A method to improve low airspeed aerodynamics of an aircraft wing having leading and trailing edges, the method comprising:
positionally fixing a planar aerodynamic device to the wing to an inboard portion of an aircraft wing laterally adjacent to a leading edge slat which defines an outboard portion of the aircraft wing so that the device is immovably positioned relative to the inboard portion of the aircraft wing during movement of the slat between a retracted position wherein inboard and outboard leading edge portions of the aircraft leading edge associated with the inboard and outboard portions of the aircraft wing, respectively, are aligned with one another whereby substantially no aerodynamic improvement of airflow over the aircraft wing between the leading and trailing edges thereof occurs, and a deployed position thereof wherein the outboard portion of the aircraft leading edge established by the slat is displaced forwardly of the inboard leading edge portion of the aircraft wing wherein improvement to airflow over the aircraft wing between the leading and trailing edges thereof occurs, and
causing the device to improve airflow over the wing between the leading and trailing edges thereof by moving the slat into the deployed position thereof.
8. A method according to claim 7 , wherein the device is positionally fixed to the wing adjacent to an inboard edge of the slat.
9. A method according to claim 7 , wherein the device has a forward end which extends beyond the aligned inboard and outboard leading edges of the inboard and outboard portions of the aircraft wing, respective, when the slat is in the retracted position thereof.