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A parasitic drag induced boundary layer reduction system and methods for reducing the boundary layer on aircraft, vehicles, and structure. The system may include a suction generator configured to utilize parasitic drag in reducing boundary layer effect and enhancing laminate flow. The suction genera

A parasitic drag induced boundary layer reduction system and methods for reducing the boundary layer on aircraft, vehicles, and structure. The system may include a suction generator configured to utilize parasitic drag in reducing boundary layer effect and enhancing laminate flow. The suction generator may include at least one of a suction port on a rearward facing surface of an aircraft, a suction vane on each wing of the aircraft, a wingtip vane on each wing of the aircraft, and a slotted tail section on a tail of the aircraft. The system may also include an induction structure configured to introduce airflow to suction created by the suction generator as the aircraft is in flight.

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1. A parasitic drag induced boundary layer reduction system for an aircraft comprising at least two wings, comprising: a suction generator configured to induce parasitic drag so as to produce suction used to lessen boundary layer effect and improve laminar airflow about the aircraft, the suction gen

1. A parasitic drag induced boundary layer reduction system for an aircraft comprising at least two wings, comprising: a suction generator configured to induce parasitic drag so as to produce suction used to lessen boundary layer effect and improve laminar airflow about the aircraft, the suction generator comprising at least one suction port on a rearward facing surface of a fuselage of the aircraft behind the at least two wings on a surface of the fuselage that also delimits a bottom surface of the aircraft, or on a tail section of the aircraft behind the at least two wings on a surface of the tail section that also delimits a bottom surface of the aircraft; andan induction panel positioned on a surface of each of the at least two wings, wherein each induction panel is in fluid communication with the at least one suction port on the fuselage or on the tail section through a communication channel between the induction panel and the at least one suction port, each induction panel comprising at least one elongated inlet slot opening into the communication channel and configured to introduce airflow into the suction generator as the aircraft is in flight. 2. The parasitic drag induced boundary layer reduction system of claim 1, wherein the suction generator further comprises at least a suction vane on each of the at least two wings of the aircraft and the induction panel comprises a leading edge portion and the elongated inlet slot is positioned with its elongated length extending lengthwise on each wing between the fuselage of the aircraft and a tip of each respective wing proximate an area of flow separation aft of the leading edge portion, the inlet slot being in fluid communication at least partially through the wing with a rearward opening on the suction vane such that airflow enters the inlet slot responsive to the suction generator as the aircraft is in flight and exits through the rearward opening of the suction vane. 3. The parasitic drag induced boundary layer reduction system of claim 2, wherein: the suction generator further comprises a wingtip vane, the wingtip vane comprising a rearward opening; andthe system further comprises a second induction panel on each of the at least two wings positioned between the suction vane and the wingtip vane, the second induction panel comprising a leading edge portion and an inlet slot proximate the leading edge portion in fluid communication with the rearward openings of the suction vane and the wingtip vane such that airflow enters the inlet slot responsive to the suction generator as the aircraft moves and exits through the rearward openings of the wingtip vane and suction vane. 4. The parasitic drag induced boundary layer reduction system of claim 3, wherein a lower section of the suction vane is configured to provide drainage for fluid entering the inlet slot of either the first or second induction panel. 5. The parasitic drag induced boundary layer reduction system of claim 4, wherein each induction panel comprises an inlet plate proximate the inlet slot, the inlet plate being movable during flight to at least partially close the inlet slot. 6. The parasitic drag induced boundary layer reduction system of claim 2, wherein the aircraft comprises an airplane and the suction vane on each wing of the airplane is separated from the induction panel on each wing of the airplane by a portion of the wing, the inlet slot being in fluid communication with the rearward opening of the suction vane through a suction channel. 7. The parasitic drag induced boundary layer reduction system of claim 2, wherein the elongated inlet slot is positioned parallel to the leading edge portion. 8. The parasitic drag induced boundary layer reduction system of claim 1, wherein the at least one suction port comprises a rearward opening in fluid communication with at least one elongated inlet slot on one of the induction panels such that airflow enters the elongated inlet slot responsive to the suction generator as the aircraft is in flight and exits through the rearward opening of the suction port. 9. The parasitic drag induced boundary layer reduction system of claim 1, wherein each of the at least one suction port comprises: at least one rearward facing cover operably coupled to the at least one suction port and configured to cover and uncover the at least one suction port; andat least one forward facing cover operably coupled to the at least one suction port and configured to cover and uncover a forward facing opening in fluid communication with the at least one suction port. 10. The parasitic drag induced boundary layer reduction system of claim 1, wherein the induction panel comprises a plurality of transverse blades extending parallel to the elongated inlet slot and further comprising a plurality of induction slots extending through the plurality of transverse blades. 11. The parasitic drag induced boundary layer reduction system of claim 10, wherein the plurality of transverse blades are each movably coupled to the induction panel and configured to assist in flight control of the aircraft through movement of the plurality of transverse blades. 12. The parasitic drag induced boundary layer reduction system of claim 1, further comprising a boundary layer skirt coupled to each wing of the aircraft, wherein the suction generator comprising a plurality of suction vanes coupled to the boundary layer skirt and the induction panel comprises a plurality of induction slots positioned on the induction panel. 13. The parasitic drag induced boundary layer reduction system of claim 1, wherein the suction port is on the rearward facing surface of the fuselage below a center of the aircraft. 14. The parasitic drag induced boundary layer reduction system of claim 1, wherein the suction port is on the tail section of the aircraft below a vertical stabilizer of the aircraft. 15. The parasitic drag induced boundary layer reduction system of claim 1, wherein the at least one suction port extends rearward on the bottom surface of the plane through a concave opening within the bottom surface of the aircraft. 16. The parasitic drag induced boundary layer reduction system of claim 1, wherein the rearward facing surface of the fuselage comprises a majority of a total length of the fuselage immediately forward of the rearward facing surface and does not extend outward of the fuselage through a fairing. 17. A method of controlling aircraft external airflow, comprising: generating parasitic drag to create suction with a suction generator on one or more rearward facing surfaces of a fuselage or a tail section of the aircraft positioned behind at least two wings of the aircraft as the aircraft moves on a surface of the fuselage or tail section that is also a bottom surface of the aircraft, the suction generator comprising at least one suction port positioned on the one or more rearward facing surfaces of the fuselage or the tail section, and at least one induction panel on each wing in fluid communication with the at least one suction port through a communication channel; andintroducing, through elongated slots on the at least one induction panel, the suction created by the suction generator to airflow as the aircraft is in flight. 18. The method of claim 17, wherein introducing, with the induction panel, the suction created by the passive suction generator to the airflow comprises introducing the airflow to the suction by directing the airflow into at least one of the elongated slots of the induction panel with a leading edge portion of the induction panel and directing the airflow out of a rearward facing opening on a suction vane in fluid communication with the inlet slot. 19. The method of claim 17, further comprising adjusting the parasitic drag of the aircraft while the aircraft is in flight by adjusting an inlet plate proximate at least one of the elongated slots to at least partially cover or uncover the at least one of the elongated slots. 20. The method of claim 19, further comprising adjusting the parasitic drag of the aircraft while the aircraft is in flight by partially or closing a forward facing opening on the suction port, the forward facing opening being in fluid communication with the suction port. 21. The method of claim 20, further comprising coupling a boundary layer skirt to each wing of the aircraft, the boundary layer skirt comprising the passive suction generator and the induction panel. 22. A parasitic drag induced boundary layer reduction system for an aircraft, comprising: a suction generator configured to induce parasitic drag so as to produce suction used to lessen boundary layer effect and improve laminar airflow about the aircraft, the suction generator comprising at least one of a suction port on a rearward facing surface of the aircraft, a suction vane on each wing of the aircraft, a wingtip vane on each wing of the aircraft, and a slotted tail section on a tail of the aircraft; andan induction panel comprising an elongated inlet slot and configured to introduce airflow to suction created by the suction generator as the aircraft is in flight;wherein the induction panel comprises a plurality of transverse blades extending parallel to the elongated inlet slot and further comprising a plurality of induction slots extending through the plurality of transverse blades; andwherein the plurality of transverse blades are each movably coupled to the induction panel and configured to assist in flight control of the aircraft through movement of the plurality of transverse blades.