Aerodynamic lifting structures having embedded engines, and associated systems and methods

An aircraft comprising a fuselage and a wing extending transversely from the fuselage, the wing having a leading portion and a trailing portion positioned opposite the leading portion along a chord of the wing, the wing further comprising:

• an upper wing portion having an upper leading edge, an upper trailing edge, and an upper exterior surface extending between the upper leading edge and the upper trailing edge, the upper exterior surface positioned to face exterior airflow above the wing;
• a lower wing portion having a lower leading edge, a lower trailing edge, and a lower exterior surface extending between the lower leading edge and the lower trailing edge, the lower exterior surface positioned to face exterior airflow below the wing;
• one or more spars extending along at least part of a span of the wing between the upper wing portion and the lower wing portion, wherein each spar of the one or more spars comprises a spar web;
• a plurality of independent ducts positioned between the upper wing portion and the lower wing portion, wherein each duct extends through an opening in at least one of the spar webs between a corresponding inlet positioned toward the leading portion and a corresponding outlet positioned toward the trailing portion, and wherein for each duct of the plurality of ducts, a cross section of the of the duct varies along a chordwise length of the duct;
• a fan positioned in each duct of the plurality of ducts, wherein the fan is rotatable to propel air received in the inlet through the duct and to the outlet;
• and
• for each fan, an electric motor or combustion engine operably connected to the fan to rotate the fan.

An aircraft comprising a fuselage and a wing extending transversely from the fuselage, the wing having a leading portion and a trailing portion positioned opposite the leading portion along a chord of the wing, the wing further comprising:

• an upper wing portion extending along at least part of a span of the wing;
• a lower wing portion extending along at least part of the span of the wing;
• a plurality of spars extending along at least a portion of the span of the wing;
• a plurality of independent ducts positioned between the upper wing portion and the lower wing portion, wherein each duct extending-extends between an inlet positioned toward a leading portion of the wing and an outlet positioned toward a trailing portion of the wing, and wherein each duct of the plurality of independent ducts extends through an opening in each spar of the plurality of spars;
• a fan positioned in each duct of the plurality of ducts, wherein the fan is positioned between a first spar of the plurality of spars and a second spar of the plurality of spars along a chordwise direction, and wherein the fan is rotatable to propel air received in the inlet through the duct and to the outlet to create thrust for the aircraft;
• and
• an aerodynamic control surface carried by the lower wing portion at the trailing portion of the wing;
• wherein:
• the aerodynamic control surface and at least part of the upper wing portion form a nozzle throat for airflow passing through at least one of the ducts;
• and
• the aerodynamic control surface is movable to change at least one of a size, shape, or position of the nozzle throat.

A wing assembly comprising:

• an upper wing portion having an upper leading edge, an upper trailing edge, and an upper exterior surface extending between the upper leading edge and the upper trailing edge, the upper exterior surface positioned to face exterior fluid flow above the wing;
• a lower wing portion having a lower leading edge spaced apart from the upper leading edge, a lower trailing edge, and a lower exterior surface extending between the lower leading edge and the lower trailing edge, the lower exterior surface positioned to face exterior fluid flow below the wing;
• a plurality of spars extending laterally along at least part of a span of the wing assembly, wherein each spar of the plurality of spars comprises a spar web;
• a plurality of independent ducts positioned between the upper wing portion and the lower wing portion, wherein each duct extends between a corresponding inlet positioned toward the leading portion and a corresponding outlet positioned toward the trailing portion, and through an opening in each spar web;
• a fan positioned in each duct of the plurality of ducts, wherein the fan is rotatable to propel fluid received in the inlet through the duct and to the outlet;
• and
• an electric motor operably connected to the fan to rotate the fan.