Uniform exhaust sheet and flow turning control

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.

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.