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Systems and methods for secondary suctioning for an aerodynamic body are presented. A primary surface is configured along a leading edge of an aerodynamic body, and at least one secondary suction device comprising an elongated shape is configured at least a first distance from the primary surface. A

Systems and methods for secondary suctioning for an aerodynamic body are presented. A primary surface is configured along a leading edge of an aerodynamic body, and at least one secondary suction device comprising an elongated shape is configured at least a first distance from the primary surface. A non-suction surface is configured between the primary surface and the at least one secondary suction device.

대표청구항 ▼

1. An apparatus for extending laminar flow over an aerodynamic surface having a primary laminar flow region, comprising: a surface skin facesheet comprising a perforated region, the perforated region comprising a plurality of perforations configured to allow a flow of a fluid through the surface ski

1. An apparatus for extending laminar flow over an aerodynamic surface having a primary laminar flow region, comprising: a surface skin facesheet comprising a perforated region, the perforated region comprising a plurality of perforations configured to allow a flow of a fluid through the surface skin facesheet;a structural core layer coupled to and configured to structurally support a portion of the surface skin facesheet, wherein a portion of the structural core layer comprise flow channels spanning a thickness of the structural core layer;a channeled stiffener positioned between the perforated region of the surface skin facesheet and the structural core layer, wherein the channeled stiffener is configured to structurally support the surface skin facesheet and channel the flow of the fluid, wherein the channeled stiffener comprises suction channels coupled to the perforated region of the surface skin face sheet, and wherein the suction channels comprise flow holes corresponding to the flow channels;an interior backing facesheet coupled to and configured to structurally support the structural core layer, wherein the interior backing facesheet comprises flow holes corresponding to the flow channels; anda suction device located a distance aft of the primary laminar flow region and configured to draw the fluid from the channeled stiffener through the flow holes in the suction channels, the flow channels in the structural core layer, and the flow holes in the interior backing facesheet. 2. The apparatus according to claim 1, wherein the perforations comprise a substantially strip-like portion of an airfoil surface along a span-wise direction. 3. The apparatus according to claim 2, wherein the surface skin facesheet is spaced a distance at least equal to a chord width of the surface skin facesheet from a leading edge of the airfoil surface. 4. The apparatus according to claim 1, wherein the channeled stiffener encloses a volume and comprises a plurality of ribs joined to a base. 5. The apparatus according to claim 1, wherein the suction device comprises at least one fixed-aft-facing-scupper passive suction source directly coupled to the surface skin facesheet. 6. The apparatus according to claim 1, further comprising a manifold coupling the interior backing facesheet to a flow control purge and suction system or a dedicated passive suction device comprising a suction port. 7. The apparatus according to claim 1, wherein the surface skin facesheet is located at least a distance from a primary suction region, a non-suction region disposed between the surface skin facesheet and a primary suction region. 8. The apparatus according to claim 1, wherein the aerodynamic surface comprises an exterior surface of a vertical fin, a horizontal stabilizer, a wing, a winglet, a fuselage skin, a canard, an elevator, an aileron, an elevon, a flap, a slat, a rudder, or a spoiler. 9. An apparatus for extending laminar flow over an aerodynamic surface, comprising: a primary laminar flow surface which provides a primary laminar flow region along an airfoil surface when the airfoil surface is moving through a fluid; anda secondary suction device located a distance from the primary laminar flow surface such that the laminar flow along the airfoil surface is extended beyond the primary laminar flow region when the airfoil surface is moving through a fluid,wherein the secondary suction device is integrated into a structural sandwich panel comprising: a surface skin facesheet comprising a perforated region,a structural core layer coupled to the surface skin facesheet,a channeled stiffener positioned between the perforated region of the surface skin facesheet and the structural core layer, andan interior backing facesheet coupled to the structural core layer. 10. The apparatus of claim 9, wherein the secondary suction device is located within the primary laminar flow region. 11. The apparatus of claim 9, further comprising a non-suction region between the primary laminar flow surface and the secondary suction device. 12. The apparatus of claim 9, wherein the secondary suction device is located starting at about 14% to about 18% of a chord line from a leading edge of the aerodynamic surface. 13. The apparatus of claim 9, wherein the primary laminar flow surface is configured for natural laminar flow operation. 14. The apparatus of claim 9, wherein the primary laminar flow surface is configured for hybrid laminar flow operation including suction applied over the primary laminar flow surface to maintain laminar flow over the primary laminar flow region, the primary laminar flow region extending a distance beyond the primary laminar flow surface. 15. The apparatus of claim 14, wherein a secondary suction mass flow rate of the secondary suction device is about 10% to about 20% of a primary suction mass flow rate at the primary laminar flow surface. 16. The apparatus of claim 9, wherein the airfoil surface is an exterior surface of one of a vertical fin, a horizontal stabilizer, a wing, a winglet, or a canard. 17. The apparatus of claim 9, further comprising a suction device in fluid communication with the channeled stiffener. 18. The apparatus of claim 17, wherein the suction device includes an aftfacing-scupper passive suction source directly coupled to the surface skin facesheet. 19. The apparatus of claim 9, further comprising: a hybrid laminar flow purge and suction system for providing suction over the primary laminar flow surface; anda manifold coupled to the backing facesheet, the manifold coupling the secondary suction device to the hybrid laminar flow purge and suction system. 20. The apparatus according to claim 9, wherein an aircraft comprises the apparatus.