Aircraft wing spoiler arrangement
View Patent ↗An aircraft wing comprising an upper surface; and two or more spoilers pivotally attached to the upper surface, wherein at least two adjacent ones of the spoilers are separated by a gap, and wherein the width of the gap is: greater than 1 cm; and sufficiently small to choke the flow of air through the gap such that for at least one flight regime with the adjacent spoilers deployed, the average air flow speed through the gap is less than 10% of the true air speed. The reduced size of the spoilers reduces the spanwise wing loading and the spoiler hinge moment, while providing a net aerodynamic effect (in terms of destroying lift over the wing) similar to that of a conventional spoiler array with no gaps.
1. An aircraft wing comprising an upper surface; and two or more spoilers pivotally attached to the upper surface, wherein at least two adjacent ones of the spoilers are separated by a gap, and wherein the width of the gap is:
a. greater than 1 cm; and
b. sufficiently small to choke the flow of air through the gap such that for at least one flight regime with the adjacent spoilers deployed, the average air flow speed through the gap is less than 10% of the true air speed.
2. The wing of claim 1 wherein the width of the gap is sufficiently small to choke the flow of air through the gap such that for at least one flight regime with the adjacent spoilers deployed, they generate flow vortices which interfere with each other.
3. The wing of claim 1 wherein the width of the gap is sufficiently small to choke the flow of air through the gap such that for at least one flight regime with the adjacent spoilers deployed, they form boundary layers which interfere with each other.
4. The wing of claim 1 wherein the width of the gap is sufficiently small to choke the flow of air through the gap such that for at least one flight regime with the adjacent spoilers deployed, the average air flow speed through the gap is less than 8% of the true air speed.
5. The wing of claim 1 wherein the width of the gap is sufficiently small to choke the flow of air through the gap such that for at least one flight regime with the adjacent spoilers deployed, the maximum air flow speed through the gap is less than 10% of the true air speed.
6. The wing of claim 1 wherein the width of the gap is sufficiently small to choke the flow of air through the gap such that for at least one flight regime with the adjacent spoilers deployed, the maximum air flow speed through the gap is less than 8% of the true air speed.
7. The wing of claim 1 wherein the smallest one of the two adjacent spoilers has a projected length L when viewed in the direction of flight of the aircraft; and wherein the width of the gap is greater than 0.1L.
8. The wing of claim 1 wherein the smallest one of the two adjacent spoilers has a projected length L when viewed in the direction of flight of the aircraft; and wherein the width of the gap is less than 0.3L.
9. The wing of claim 1 wherein the width of the gap is less than 50 cm.
10. The wing of claim 1 wherein the gap is defined by a pair of opposing sides of the adjacent spoilers; and each side has one or more projections or recesses.
11. The wing of claim 1 wherein the width of the gap is adjustable in-flight.
12. A method of operating an aircraft wing comprising an upper surface and two or more spoilers pivotally attached to the upper surface, wherein at least two adjacent ones of the spoilers are separated by a gap having a width greater than 1 cm, the method comprising:
a. moving the aircraft relative to an air mass at a true air speed; and
b. pivoting the adjacent spoilers into a deployed position in which the average air flow speed through the gap is less than 10% of the true air speed.
13. The method of claim 12 wherein the gap has a width which is sufficiently small such that the average air flow speed through the gap is less than 8% of the true air speed.
14. An aircraft wing comprising an upper surface and two or more spoilers pivotally attached to the upper surface, wherein the geometry of and separation between the spoilers is adapted so that for at least one flight regime, when adjacent spoilers are deployed, they generate flow vortices which destructively interfere with each other.