Uniform exhaust sheet and flow turning control
An aircraft may comprise propulsors. The propulsors may be integrated into an array of propulsors. An array of propulsors may be integrated in an airfoil of the aircraft. The aircraft may include a flow turning control system. The flow turning control system may include an end wall and one or more movable flaps. The flow turning control system may enable selective flow turning of the flow of propelled by the array of propulsors. The selective flow turning may include actuating the one or more movable flaps. The selective flow turning may achieve flow turning of over a trailing edge of a movable flap.
1 . An aircraft comprising:
an array of propulsors defining an exhaust area, wherein the array of propulsors is positioned on an upper surface of a wing of the aircraft and at a leading edge of the wing;
a flow turning control system configured to control turning of a flow of air propelled across the upper surface of the wing by the array of propulsors, the flow turning control system comprising:
an end wall defining a terminal end of the array of propulsors;
a first movable flap attached to the array of propulsors aftward of the exhaust area and above the wing of the aircraft, wherein the first movable flap is configured to provide a ratio, between a height of the end wall and a height of the exhaust area, that is at least 1.5 and up to 2.0; and
a second movable flap attached to the wing of the aircraft aftward of the exhaust area, wherein the second movable flap is configured to provide a ratio, between a length of the second movable flap and the height of the exhaust area, that is between 2 and 10;
wherein the flow turning control system enables selective flow turning of the flow of air over a trailing edge of the second movable flap of at least 90 degrees and up to 180 degrees; and
a non-transitory computer-readable medium comprising computer-executable instructions that, when executed by one or more processors, cause the one or more processors to:
receive an input signal indicating an adjustment to the flow turning of the flow of air; and
cause adjustment to the flow turning of the flow of air at least by actuating, based on the input signal, one or more of the first movable flap or the second movable flap.
2 . The aircraft of claim 1 , wherein the flow turning control system further enables the selective flow turning with a ratio between actual thrust and ideal thrust of at least 70 percent and up to 90 percent.
3 . The aircraft of claim 1 , wherein the exhaust area comprises a contracting exhaust area.
4 . The aircraft of claim 1 , wherein the height of the end wall comprises a first height at a first position of the end wall and a second height, different than the first height, at a second position of the end wall that is aftward of the first position.
5 . The aircraft of claim 1 , wherein the flow turning control system further comprises a first radius of curvature of the second movable flap at an articulatable edge of the second movable flap and a second radius of curvature of the second movable flap, different than the first radius of curvature, at a trailing edge of the second movable flap.
6 . The aircraft of claim 1 , wherein the end wall comprises:
a boom positioned at an edge of the wing; or
a portion of a fuselage of the aircraft.
7 . The aircraft of claim 1 , wherein the end wall extends from an articulatable edge of the first movable flap to the trailing edge of the second movable flap.
8 . The aircraft of claim 1 , wherein the end wall extends in a direction aftward of the exhaust area across an upper surface of the wing and across an upper surface of the second movable flap.
9 . The aircraft of claim 1 , wherein the first movable flap is configured to extend, away from the exhaust area, a maximum distance that is less than a distance between the exhaust area and an articulatable edge of the second movable flap.
10 . The aircraft of claim 1 , wherein the flow turning control system further enables at least one of:
selective flow turning of the flow of air over the trailing edge of the second movable flap of at least 45 degrees and up to 60 degrees with a ratio between actual thrust and ideal thrust of at least 90 percent and up to 100 percent; or
selective flow turning of the flow of air over the trailing edge of the second movable flap of at least 60 degrees and up to 90 degrees with a ratio between actual thrust and ideal thrust of at least 80 percent and up to 100 percent.
11 . The aircraft of claim 1 , wherein the height of the exhaust area is an instantaneous exhaust height that is based on a position, of the first movable flap, between a first maximum position of the first movable flap and a second maximum position, opposite the first maximum position, of the first movable flap.
12 . An aircraft comprising:
an array of propulsors defining an exhaust area, wherein the array of propulsors is positioned on an upper surface of a wing of the aircraft and at a leading edge of the wing;
a flow turning control system configured to control turning of a flow of air propelled across the upper surface of the wing by the array of propulsors, the flow turning control system comprising:
an end wall defining a terminal end of the array of propulsors, wherein the end wall has an end wall height providing a ratio, between the end wall height and a reference height of the exhaust area, that is at least 1.5 and up to 2.0;
a first movable flap attached to the array of propulsors aftward of the exhaust area and above the wing of the aircraft, wherein the reference height is measured between a trailing edge of the first movable flap in an undeflected position and the upper surface of the wing;
wherein the first movable flap is configured to modify an instantaneous exhaust height of the exhaust area that is based on a position, of the first movable flap, between a first maximum position of the first movable flap and a second maximum position, opposite the first maximum position, of the first movable flap; and
a second movable flap attached to the wing of the aircraft aftward of the exhaust area, wherein the second movable flap has a length providing a ratio, between the length of the second movable flap and the reference height, that is between 2 and 10;
wherein the flow turning control system enables selective flow turning of the flow of air over a trailing edge of the second movable flap of:
at least 90 degrees and up to 180 degrees with a ratio between actual thrust and ideal thrust of at least 70 percent and up to 90 percent;
at least 60 degrees and up to 90 degrees with a ratio between actual thrust and ideal thrust of at least 80 percent and up to 100 percent; and
at least 45 degrees and up to 60 degrees with a ratio between actual thrust and ideal thrust of at least 90 percent and up to 100 percent; and
a non-transitory computer-readable medium comprising computer-executable instructions that, when executed by one or more processors, cause the one or more processors to:
receive an input signal indicating an adjustment to the flow turning of the flow of air; and
cause adjustment to the flow turning of the flow of air at least by actuating, based on the input signal, one or more of the first movable flap or the second movable flap.
13 . The aircraft of claim 12 , wherein the exhaust area comprises a contracting exhaust area.
14 . The aircraft of claim 12 , wherein end wall height comprises a first height at a first position of the end wall and a second height, different than the first height, at a second position of the end wall that is aftward of the first position.
15 . The aircraft of claim 12 , wherein the first movable flap is configured to extend, away from the exhaust area, a maximum distance that is less than a distance between the exhaust area and an articulatable edge of the second movable flap.
16 . An aircraft comprising:
an array of propulsors defining an exhaust area, wherein the array of propulsors is positioned on an upper surface of a wing of the aircraft and at a leading edge of the wing;
a flow turning control system configured to control turning of a flow of air propelled across the upper surface of the wing by the array of propulsors, the flow turning control system comprising:
an end wall defining a terminal end of the array of propulsors, wherein the end wall has an end wall height providing a ratio, between the end wall height and a reference height of the exhaust area, that is at least 0.5 and up to 1.0;
a first movable flap attached to the array of propulsors aftward of the exhaust area and above the wing of the aircraft, wherein the reference height is measured between a trailing edge of the first movable flap in an undeflected position and the upper surface of the wing; and
a second movable flap attached to the wing of the aircraft aftward of the exhaust area, wherein the second movable flap has a length providing a ratio, between the length of the second movable flap and the reference height, that is between 2 and 10;
wherein the flow turning control system enables selective flow turning of the flow of air over a trailing edge of the second movable flap of:
at least 90 degrees and up to 180 degrees with a ratio between actual thrust and ideal thrust of at least 70 percent and up to 90 percent;
at least 60 degrees and up to 90 degrees with a ratio between actual thrust and ideal thrust of at least 80 percent and up to 100 percent; and
at least 45 degrees and up to 60 degrees with a ratio between actual thrust and ideal thrust of at least 90 percent and up to 100 percent; and
a non-transitory computer-readable medium comprising computer-executable instructions that, when executed by one or more processors, cause the one or more processors to:
receive an input signal indicating an adjustment to the flow turning of the flow of air; and
cause adjustment to the flow turning of the flow of air at least by actuating, based on the input signal, one or more of the first movable flap or the second movable flap.
17 . The aircraft of claim 16 , wherein the exhaust area comprises a contracting exhaust area.
18 . The aircraft of claim 16 , wherein the end wall height comprises a first height at a first position of the end wall and a second height, different than the first height, at a second position of the end wall that is aftward of the first position.
19 . The aircraft of claim 16 , wherein the first movable flap is configured to extend, away from the exhaust area, a maximum distance that is less than a distance between the exhaust area and an articulatable edge of the second movable flap.
20 . The aircraft of claim 16 , wherein the first movable flap is configured to provide, by moving between a first position and a second position:
a ratio, between the end wall height and an instantaneous height of the exhaust area, between 0.5 and 1.0;
a ratio, between a flap radius of the second movable flap and the instantaneous height of the exhaust area, that is at least 1 and up to 2; and
a ratio, between the length of the second movable flap and the instantaneous height of the exhaust area, that is between 2 and 10.