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A dual channel wing for an aircraft, comprising an inboard and an outboard portion, wherein each portion comprises a channel wing section. Each channel may include a propulsor and the propulsors of each of the channels may be offset relative to one another in the chordwise direction of the wing. The

A dual channel wing for an aircraft, comprising an inboard and an outboard portion, wherein each portion comprises a channel wing section. Each channel may include a propulsor and the propulsors of each of the channels may be offset relative to one another in the chordwise direction of the wing. The wing may be foldable upon itself about a chordwise axis such that the inboard and outboard channels overlap. At least one dual channel wing may also be located on an aerocar.

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1. A wing comprising: an inboard portion;an outboard portion;a first channel located in the outboard portion of the wing;a second channel located in the inboard portion of the wing;a first propulsor located along an axis of the first channel;a second propulsor located along an axis of the second cha

1. A wing comprising: an inboard portion;an outboard portion;a first channel located in the outboard portion of the wing;a second channel located in the inboard portion of the wing;a first propulsor located along an axis of the first channel;a second propulsor located along an axis of the second channel; anda control surface;wherein one of the first and second propulsors is located near a trailing edge of the wing and the other of the first and second propulsors is forwardly offset on the respective axis towards a leading edge of the wing; andwherein the control surface is located within the channel of the forwardly offset propulsor and is located downstream from the forwardly offset propulsor. 2. The wing according to claim 1, wherein the first propulsor is the propulsor that is forwardly offset and the control surface is located within the first channel; and wherein the control surface is an aileron. 3. The wing according to claim 1, wherein the inboard and outboard portions are arranged side-by-side along a span of the wing; and wherein the wing is configured to fold about a chordwise axis located between the channels such that the outboard portion is stowed atop the inboard portion in the folded configuration. 4. The wing according to claim 3, wherein the first and second channels form a tube when in the folded configuration; and wherein the first and second propulsors and the control surface are all located within the tube when in the folded configuration. 5. The wing according to claim 4, wherein the folded inboard and outboard portions are configured to pivot as a unit about a substantially vertical axis near a root of the wing. 6. The wing according to claim 1, further comprising: a blown channel circulation control wing (CCW) system. 7. The wing according to claim 6, wherein the blown channel CCW system includes: a leading edge air supply plenum; andat least one leading-edge slot;wherein the plenum is configured to supply the at least one slot with pressurized air; andwherein the at least one slot is configured to discharge the pressurized air over an upper surface of the wing. 8. The wing according to claim 7, wherein the blown channel CCW system further includes: a trailing edge air supply plenum; andat least one trailing-edge slot;wherein the trailing edge plenum is configured to supply the at least one trailing edge slot with pressurized air; andwherein the at least one trailing edge slot is configured to discharge the pressurized air downstream of the trailing edge of the wing. 9. The wing according to claim 6, wherein the blown channel CCW system further includes: a trailing edge air supply plenum; andat least one trailing-edge slot;wherein the trailing edge plenum is configured to supply the at least one trailing edge slot with pressurized air; andwherein the at least one trailing edge slot is configured to discharge the pressurized air downstream of the trailing edge of the wing. 10. The wing according to claim 1, wherein the first and second propulsors each comprise a propeller. 11. An aerocar comprising: at least one wing according to claim 1. 12. A dual channel wing comprising: an inboard channel section; andan outboard channel section;wherein the inboard and outboard channel sections are arranged side-by-side along a span of the wing; andwherein the wing is configured to fold about a chordwise axis located between the channel sections such that the outboard channel section is stowed atop the inboard channel section. 13. The dual channel wing according to claim 12, further comprising: a first propeller;a second propeller; andan aileron;wherein the first propeller is located along an axis of the outboard channel section and the second propeller is located along an axis of the inboard channel section;wherein one of the first and second propellers is located towards a trailing edge of the wing and the other of the first and second propellers is forwardly offset on its respective axis towards a leading edge of the wing; andwherein the aileron is located within the channel of the forwardly offset propeller and is located downstream from the forwardly offset propeller. 14. An aerocar comprising: a fuselage; andat least one dual channel wing according to claim 13;wherein the at least one dual channel wing is connected to the fuselage. 15. The aerocar according to claim 14, wherein the folded inboard and outboard sections are configured to pivot as a unit about a substantially vertical axis near a root of the at least one wing so as to be stowed substantially within a width dimension of the fuselage. 16. The dual channel wing according to claim 12, further comprising: a blown channel circulation control wing (CCW) system; wherein the blown channel CCW system includes: a leading edge air supply plenum; andat least one leading-edge slot;wherein the plenum is configured to supply the at least one slot with pressurized air; andwherein the at least one slot is configured to discharge the pressurized air over an upper surface of the at least one wing. 17. The dual channel wing according to claim 16, wherein the blown channel CCW system further includes: a trailing edge air supply plenum; andat least one trailing-edge slot;wherein the trailing edge plenum is configured to supply the at least one trailing edge slot with pressurized air; andwherein the at least one trailing edge slot is configured to discharge the pressurized air downstream of a trailing edge of the at least one wing. 18. The dual channel wing according to claim 12, further comprising: a blown channel circulation control wing (CCW) system; wherein the blown channel CCW system further includes: a trailing edge air supply plenum; andat least one trailing-edge slot;wherein the trailing edge plenum is configured to supply the at least one trailing edge slot with pressurized air; andwherein the at least one trailing edge slot is configured to discharge the pressurized air downstream of a trailing edge of the at least one wing. 19. A method of stowing and deploying at least one dual channel wing on an aerocar, the method comprising: providing an aircraft comprising: a fuselage; andat least one dual channel wing; wherein the at least one dual channel wing comprises: an inboard channel section; andan outboard channel section;wherein the inboard and outboard channel sections are arranged side-by-side along the span of the at least one wing;wherein the at least one wing is configured to fold about a chordwise axis such that the outboard channel section is stowed atop the inboard channel section;swinging the outboard channel section about the chordwise axis such that the outboard channel section stows atop the inboard channel section to place the channel sections in a stowed state; andswinging the outboard channel section, from the stowed state, about the chordwise axis such that the outboard channel section and the inboard channel section are unfolded and arranged side-by-side to place the channel sections in a deployed state. 20. The method of stowing and deploying a dual channel wing according to claim 19, wherein, when folded, the inboard and outboard sections are configured to pivot as a unit about a substantially vertical axis near a root of the at least one wing, and the method further comprising: pivoting the folded inboard and outboard sections as a unit about the substantially vertical axis such that the at least one wing is located substantially within a width dimension of the fuselage to place the at least one wing in a stowed state; andpivoting the at least one stowed wing from substantially within the width dimensions of the fuselage about the substantially vertical axis prior to unfolding the channel sections into a deployed state.