# US 2021/0331784 A1 · High Efficiency Low Power (HELP) Active Flow Control Methodology for Simple-Hinged Flap High-Lift Systems > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2021/0331784 A1 - Document ID: US20210331784A1 - Status: Published application - Kind: A1 - Application number: 17/238,443 - Filed: 2021-04-23 - Published: 2021-10-28 - Earliest claimed: 2020-04-23 - Assignees: United States of America as represented by the Administrator of NASA - Applicants: United States of America AS Represented By the Administrator of Nasa - Inventors: John C. Lin; Latunia P. Melton; Mehti Koklu; Marlyn Y. Andino - Web page: https://patentgrep.com/patent/US20210331784A1 ## CPC - B64C 9/18: by single flaps - B64C 9/02: Mounting or supporting thereof - B64C 9/16: at the rear of the wing - B64C 13/40: using fluid pressure - B64C 21/04: for blowing - B64D 41/00: Power installations for auxiliary purposes - Y02T 50/10: Drag reduction - Y02T 50/30: Wing lift efficiency - Y02T 50/40: Weight reduction - B64C: AEROPLANES; HELICOPTERS - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A simple-hinged flap assembly for a winged aircraft includes a simple-hinged flap having a leading airfoil section pivotably connected to a trailing airfoil section via a hinge, and an active flow control (AFC) actuator assembly. The assembly is connected to or integrally formed with the flap and includes upstream and downstream AFC actuators arranged in respective first and second rows, and collectively configured to provide first and second outlet mass flowrates. The downstream AFC actuators emit the second outlet mass flowrate at a rate that substantially exceeds the first outlet mass flowrate, such that the first outlet mass flowrate preconditions a boundary layer around the simple-hinged flap assembly. A winged aircraft includes a pneumatic power supply, fuselage, a wing connected to the fuselage, and the simple-hinged flap assembly. ## Claims ### Claim 1 A simple-hinged flap assembly for a winged aircraft, comprising: a simple-hinged flap having a leading airfoil section that is pivotably connected to a trailing airfoil section via an intervening hinge; and an active flow control (AFC) actuator assembly connected to or integrally formed with the simple-hinged flap, the AFC actuator assembly including: a row of upstream AFC actuators collectively configured to provide a first outlet mass flowrate; and a row of downstream AFC actuators spaced apart from the row of upstream AFC actuators, wherein the row of downstream AFC actuators is configured to provide a second outlet mass flowrate that substantially exceeds the first outlet mass flowrate, such that the first outlet mass flowrate preconditions a boundary layer around the simple-hinged flap assembly when the winged aircraft is in flight. ### Claim 2 (depends on 1) The simple-hinged flap assembly of claim 1, wherein the winged aircraft includes a pneumatic power supply, the AFC actuator assembly is in fluid communication with the pneumatic power supply and configured to receive an inlet mass flowrate therefrom, and the row of downstream AFC actuators includes fluidic actuators configured to provide the second output mass flowrate in response to the inlet mass flowrate. ### Claim 3 (depends on 2) The simple-hinged flap assembly of claim 2, wherein the AFC actuator assembly defines therein a pneumatic feed tube connectable to the pneumatic power supply, and a plenum chamber in fluid communication with each of the pneumatic feed tube, the row of upstream AFC actuators, and the row of downstream AFC actuators. ### Claim 4 (depends on 3) The simple-hinged flap assembly of claim 3, wherein the row of upstream AFC actuators includes fluidic oscillators. ### Claim 5 (depends on 3) The simple-hinged flap assembly of claim 3, wherein the row of downstream AFC actuators includes steady-blowing jet nozzles. ### Claim 6 (depends on 1) The simple-hinged flap assembly of claim 1, wherein the AFC actuator assembly including an actuator housing defining therein the row of upstream AFC actuators and the row of downstream AFC actuators. ### Claim 7 (depends on 1) The simple-hinged flap assembly of claim 1, wherein the AFC actuator assembly includes a floor connectable to the simple-hinged flap, an end wall arranged radially with respect to the floor, spanwise internal supporting walls, and a curved upper wall connected to the end wall and tapering toward a distal end of the floor, wherein the curved upper wall defines the row of upstream AFC actuators, and wherein the floor, the spanwise internal supporting walls, and the curved upper wall together define the row of downstream AFC actuators. ### Claim 8 (depends on 7) The simple-hinged flap assembly of claim 7, wherein the end wall defines a pneumatic feed tube configured to connect to a pneumatic power supply of the winged aircraft. ### Claim 9 A winged aircraft comprising: a pneumatic power supply; a fuselage; a wing connected to the fuselage; and a simple-hinged flap assembly connected to the wing and having: a simple-hinged flap having a leading airfoil section that is pivotably connected to a trailing airfoil section via an intervening hinge; and at least one active flow control (AFC) actuator assembly connected to or integrally formed with the simple-hinged flap, wherein the AFC actuator assembly is in fluid communication with the pneumatic power supply and receives an inlet mass flowrate therefrom, and includes: an upstream array of fluidic oscillators arranged in a first row, and collectively configured to emit a first outlet mass flowrate in response to the inlet mass flowrate; a downstream array of steady-blowing jet nozzles spaced apart from the upstream array of fluidic oscillators and arranged in a second row, wherein the downstream array of steady-blowing jet nozzles is collectively configured to emit a second outlet mass flowrate that substantially exceeds the first outlet mass flowrate, such that the first outlet mass flowrate preconditions a boundary layer around the simple-hinged flap assembly when the winged aircraft is in flight. ### Claim 10 (depends on 9) The winged aircraft of claim 9, wherein the leading airfoil section and the trailing airfoil section are arranged in an upstream tangent plane and a downstream tangent plane of the simple-hinged flap assembly, respectively, the first row is situated in the upstream tangent plane, and the second row is situated in the downstream tangent plane. ### Claim 11 (depends on 9) The winged aircraft of claim 9, wherein the at least one AFC actuator assembly includes an actuator housing defining therein the upstream array of fluidic oscillators and the downstream array of steady-blowing jet nozzles. ### Claim 12 (depends on 11) The winged aircraft of claim 11, wherein the at least one AFC actuator assembly defines therein a pneumatic feed tube connected to the pneumatic power supply, and a plenum chamber in fluid communication with each of the pneumatic feed tube, the upstream array of fluidic oscillators, and the downstream array of steady-blowing jet nozzles. ### Claim 13 (depends on 12) The winged aircraft of claim 12, wherein the housing includes a floor connectable to the simple-hinged flap, an end wall arranged radially with respect to the floor, spanwise internal supporting walls, and a curved upper wall connected to the end wall and tapering toward a distal end of the floor, wherein the curved upper wall defines the upstream row of fluidic oscillators therein, and wherein the floor, the spanwise internal supporting walls, and the curved upper wall together define the downstream array of steady-blowing jet nozzles. ### Claim 14 (depends on 13) The winged aircraft of claim 13, wherein the end wall defines, as the pneumatic feed tube, a single cylindrical pneumatic feed tube that is connected to the pneumatic power supply. ### Claim 15 (depends on 9) The winged aircraft of claim 9, wherein the pneumatic power supply includes a compressor, engine bypass air, and/or an auxiliary power unit. ### Claim 16 (depends on 9) The winged aircraft of claim 9, wherein the simple-hinged flap includes an inboard section and an outboard section, the at least one AFC actuator assembly includes a first plurality of AFC actuator assemblies arranged on or within the inboard section, and a second plurality of AFC actuator assemblies arranged on or within the outboard section. ### Claim 17 An active flow control (AFC) actuator assembly for a simple-hinged flap aboard an aircraft having a pneumatic power supply, the simple-hinged flap having a leading airfoil section that is pivotably connected to a trailing airfoil section via an intervening hinge, the AFC actuator assembly comprising: a housing defining a plenum chamber and a pneumatic feed tube configured to connect to the pneumatic power supply, thereby receiving an inlet mass flowrate from the pneumatic power supply, wherein the housing is connectable to or integrally formed with the simple-hinged flap; an upstream array of fluidic oscillators arranged in a first row, and collectively configured to emit a first outlet mass flowrate in response to the inlet mass flowrate; and a downstream array of steady-blowing jet nozzles spaced apart from the upstream array of fluidic oscillators, and arranged in a second row downstream of the first row, wherein the downstream array of steady-blowing jet nozzles is collectively configured to emit a second outlet mass flowrate that substantially exceeds the first outlet mass flowrate, such that the first outlet mass flowrate preconditions a boundary layer around the simple-hinged flap when the winged aircraft is in flight. ### Claim 18 (depends on 17) The AFC actuator assembly of claim 17, wherein the housing defines therein the upstream array of fluidic oscillators and the downstream array of steady-blowing jet nozzles. ### Claim 19 (depends on 17) The AFC actuator assembly of claim 17, wherein the leading airfoil section and the trailing airfoil section are arranged in an upstream tangent plane and a downstream tangent plane of the AFC actuator assembly, respectively, the first row is situated in the upstream tangent plane, and the second row is situated in the downstream tangent plane. ### Claim 20 (depends on 17) The AFC actuator assembly of claim 17, wherein the housing includes a floor connectable to the simple-hinged flap, an end wall arranged radially with respect to the floor, spanwise internal supporting walls, and a curved upper wall connected to the end wall and tapering toward a distal end of the floor, wherein the curved upper wall defines the upstream array of fluidic oscillators therein, and wherein the floor, the spanwise internal supporting walls, and the curved upper wall together define the downstream array of steady-blowing jet nozzles.