Hybrid flow control method for simple hinged flap high-lift system

Patent metadata

Field	Value
Publication number	US-10358208-B2
Application number	US-201514955913-A
Country	US
Kind code	B2
Filing date	Dec 1, 2015
Priority date	Dec 1, 2014
Publication date	Jul 23, 2019
Grant date	Jul 23, 2019

Abstract

Systems, methods, and devices are provided that provide hybrid flow control for a simple hinged flap high-lift system using sweeping jet (SWJ) actuators for active flow control (AFC) and adaptive vortex generators (AVGs) that may be actuated by flap deflection for passive flow control (PFC). The various embodiments may significantly reduce mass flow, differential pressure, and power requirements for equivalent flow control performance when compared to using AFC only. The various embodiments may reduce the power requirement of AFC, while still maintaining the aerodynamic performance enhancement necessary for high-lift applications using a simple hinged flap. The various embodiments may provide the necessary lift enhancement for a simple hinged flap high-lift system, while keeping the pneumatic power requirement (mass flow and pressure) for the AFC within an aircraft's capability for system integration.

First claim

What is claimed is:

1. A wing, comprising:
a main element with posing leading and trailing edges;
at least one trailing-edge, flap movably attached to and deflectable from the main element proximate the trailing edge thereof;
at least one passive flow control (PFC) device installed, fixed and/or formed on the main element at the trailing edge thereof; and
at least one active flow control (AFC) device include on the main element and located upstream of the PFC device, the AFC device being configured to provide a high-momentum boundary-layer flow toward the PFC device.

2. The wing of claim 1 , wherein the PFC device is a vortex generator (VG).

3. The wing of claim 2 , wherein the VG is a flap-actuated vortex generator (FAVG) located at a leading edge of the flap.

4. The wing of claim 3 , wherein the AFC device is a sweeping jet (SWJ) actuator.

5. The wing of claim 3 , wherein the AFC device is selected from the group comprising a steady AFC device blowing through a spanwise slot, a steady AFC device blowing through a spanwise discrete nozzle, an unsteady blowing pulsed jet, an unsteady plasma actuator, an unsteady synthetic jet, and an unsteady fluidic nozzle.

6. The wing of claim 2 , wherein the VG is an adaptive vortex generator (AVG).

7. The wing of claim 6 , wherein the AFC device is located within the main element, and wherein the AVG is located along a hinged line between the trailing-edge gain and the main element.

8. The wing of claim 6 , wherein the AFC device includes a first sweeping jet (SWJ) actuator located upstream of the AVG and a second SWJ actuator located downstream of the AVG.

9. The wing of claim 8 , wherein the second SWJ actuator is located downstream of the AVG on the trailing-edge flap, and wherein the AVG is located along a hinged line between the trailing-edge flap and the main element.

10. The wing of claim 6 , wherein the AFC device is located upstream of the AVG on a drooped leading edge or leading-edge flap, and wherein the AVG is located along the hinged line between the trailing-edge flap and the main element.

11. The wing of claim 6 , wherein the AFC device is selected from the group comprising a sweeping jet (SWJ) actuator, a steady AFC device blowing through a spanwise slot, a steady AFC device blowing through a spanwise discrete nozzle, an unsteady blowing pulsed jet, an unsteady plasma actuator, an unsteady synthetic jet, and an unsteady fluidic nozzle.

12. The wing of claim 6 , wherein:
the AFC device is a plurality of SWJ actuators; and
at least one of the plurality of SWJ actuators is located upstream of the AVG, at least one of the plurality of SWJ actuators is located downstream of the AVG, and at least one of the plurality of SWJ actuators is located at a hinge line side-by-side with the AVG.

13. The wing of claim 1 , wherein the PTV device includes a vortex generator (VG) with a plurality of VG vanes spaced from one another spanwise along a span of the main element, the plurality of VG vanes being angled off center of the wing in a counter-rotating, pattern.

14. The wing of claim 1 , wherein the PFC device includes a vortex generator (VG) with a plurality of VG vanes spaced from one another spanwise along a span of the main element, the plurality of VG vanes being angled off center of the wing in a co-rotating pattern.

15. The wing of claim 1 , wherein the AFC device includes a sweeping jet (SWJ) actuator located within the main element, the SWJ actuator including a supply nozzle through which air enters and is compressed, an interacting region within which the compressed air curves, a feedback channel through which a recycled portion of the air is guided to a control region interposed between the supply nozzle and the interacting region, and an outlet nozzle through which air exits the SWI actuator in a jet that flips from one side of the outlet nozzle to the other.

16. A vehicle, comprising:
a wing, comprising:
a main element with opposing leading and trailing edges;
at least one trailing-edge flap movably attached to and deflectable from the main element proximate the trailing edge thereof;
at least one passive flow control (PFC) device installed, fixed and/or formed on the main element at the trailing edge thereof; and
at least one active flow control (AFC) device included on the main element and located upstream of the PFC device, the AFC device being configured to provide a high-momentum boundary-layer flow toward the PFC device.

17. The vehicle of claim 16 , wherein the PFC, device is a vortex generator (VG).

18. The vehicle of claim 17 . wherein the VG is a flap-actuated vortex generator (FAVG) located at a leading edge of the flap.

19. The vehicle of claim 18 , wherein the AFC device is selected from the group comprising a sweeping jet (SWJ) actuator, a steady AFC device blowing through a spanwise slot, a steady AFC device blowing through a spanwise discrete nozzle, an unsteady blowing pulsed jet, an unsteady plasma actuator, an unsteady synthetic jet, and an unsteady fluidic nozzle.

20. The vehicle of claim 19 , wherein the VG is an adaptive vortex generator (AVG).

Assignees

• Nasa
• Nasa

Inventors

• Lin John C
• Koklu Mehti

Classifications

• B64C3/50

  by leading or trailing edge flaps · CPC title

• B64C23/06 Primary

  by generating vortices · CPC title

• B64C9/16

  at the rear of the wing · CPC title

• B64C21/04

  for blowing · CPC title

• B64C21/08

  adjustable · CPC title