초록 ▼

The present invention provides flow field control techniques that adapt the aft body region flow field to eliminate or mitigate the development of massive separated flow field zones and associated unsteady vortical flow field structures. Embodiments of the present invention use one or more distribut

The present invention provides flow field control techniques that adapt the aft body region flow field to eliminate or mitigate the development of massive separated flow field zones and associated unsteady vortical flow field structures. Embodiments of the present invention use one or more distributed arrays of flow control devices (submerged in the boundary layer) to create disturbances in the flow field that inhibit the growth of larger vortical structures and/or to energize the aft body shear layer to keep the shear layer attached the aft body surface. These undesirable aerodynamic phenomena produce increased vehicle drag which harms vehicle range, persistence, and loiter capabilities. Additionally, the unsteady nature of the turbulent vortical structures shed in the aft body wake region may produce increased dynamic buffeting and aft body heating by entraining nozzle jet exhaust (a.k.a. jet wash) —requiring additional structural support, shielding, and vehicle weight.

대표청구항 ▼

What is claimed is: 1. A method to suppress flow field separation within an aft body flow field, comprising: placing at least one upstream array of flow control devices proximate to an aerodynamic surface of an aft portion of an aircraft above and proximate to an engine exhaust port of the aircraft

What is claimed is: 1. A method to suppress flow field separation within an aft body flow field, comprising: placing at least one upstream array of flow control devices proximate to an aerodynamic surface of an aft portion of an aircraft above and proximate to an engine exhaust port of the aircraft, and at least one downstream array of flow control devices proximate to an aerodynamic surface below the engine exhaust port of the aircraft; inducing secondary flow structures within a boundary layer of the fluid flow with the flow control devices, to suppress flow field separation and reduces buffeting, fatigue and/or jet wash of the aircraft. 2. The method of claim 1, wherein suppressing flow field separation aids in dynamically controlling the aircraft. 3. The method of claim 1, further comprising: sensing flow conditions proximate to the engine exhaust port with a flow sensor system; and dynamically controlling the upstream and downstream arrays to produce a desired aft body flow field. 4. The method of claim 1, wherein the upstream and downstream arrays of flow control devices inject momentum into a near-wall boundary region. 5. The method of claim 1, wherein the upstream and downstream arrays of flow control devices comprises micro fabricated mechanical structures. 6. A flow control system surface operable to suppress flow field separation within a receptive zone on an aircraft having an engine submerged within a body of the aircraft, wherein the flow control system surface comprises: an upstream array of flow control devices located substantially upstream of fluid flow over the receptive zone upstream, above and proximate to an engine exhaust port, and a downstream, below array of flow control devices located downstream and proximate to the engine exhaust port, wherein the upstream and downstream arrays introduces secondary flows in a near wall boundary layer, wherein the secondary flows effect an inception location and trajectory of flow field vortical structure over the receptive zone; and a controller operably coupled to the upstream and downstream arrays of flow control devices, wherein the controller system directs the upstream and downstream arrays of flow control devices to introduce the secondary flows to achieve a desired fluid flow over the receptive zone. 7. The flow control system surface of claim 6, further comprising: a sensing system operably coupled to the controller, wherein the sensing system detects fluid flow characteristics over the receptive zone. 8. The flow control system surface of claim 7, wherein the control system: compares the detected fluid flow characteristics over the receptive zone to the desired fluid flow over the receptive zone; and directs the upstream and downstream arrays of flow control devices to introduce the secondary flows to achieve the desired fluid flow over the receptive zone based on the comparison. 9. The flow control system surface of claim 6, wherein the desired fluid flow reduces downstream fatigue, buffeting, and/or jet wash. 10. The flow control system surface of claim 6, wherein the upstream and downstream arrays of flow control device-s comprises active flow control devices. 11. The flow control system surface of claim 6, wherein the upstream and downstream arrays of flow control devices comprises micro-jets. 12. The flow control system surface of claim 11, wherein the micro-jets comprise synthetic pulsators. 13. The flow control system surface of claim 6, wherein the upstream and downstream arrays of flow control devices comprises micro-fabricated mechanical structures. 14. An aircraft having an engine submerged within a body of the aircraft, and a receptive zone located adjacent an engine exhaust port that forms an aft body aerodynamic control surface for manipulating flow field vortices over the aft body aerodynamic control surface, wherein the aerodynamic control surface comprises: an upstream array of micro jets located substantially upstream of fluid flow over the aerodynamic surface above and proximate to an engine exhaust port of the aircraft, and a downstream array of micro jets proximate to an aerodynamic surface below the engine exhaust port of the aircraft, wherein the upstream and downstream arrays of micro jets introduce secondary flows structures within a boundary layer of the fluid flow, wherein the secondary flows reduces flow field separation over the aft body aerodynamic control surface; and a control system operably coupled to the upstream and downstream arrays of micro jets, wherein the control system directs the upstream and downstream arrays of micro jets to introduce secondary flows in order to achieve a desired flow field over the aft body aerodynamic control surface. 15. An aft body region of an aircraft having a blended wing body with an engine submerged in the blended wing body, and reduced structural requirements comprising: an upstream array of flow control devices located substantially upstream and proximate to the aft body region of the aircraft and upstream, above and proximate to an engine exhaust port of the aircraft, and a downstream, below array of flow control devices located downstream and proximate to the engine exhaust port, the aft body region having a substantially continuous surface, the upstream and downstream arrays of flow control devices introducing secondary flows in a near wall boundary layer, wherein the secondary flows suppress flow field separation within an aft body flow field; and wherein suppressed flow field separation within the aft body flow field is operable to reduce buffeting, fatigue and/or jet wash proximate to the aft body region.