Abstract: The fluid-dynamic structure comprises a fluid-dynamic exterior having a flow-augmented surface and a passive drag reduction system comprising a flow-repositioning duct having an inlet and an outlet that extend through the fluid-dynamic exterior. Under operative conditions, the passive drag reduction system is configured to direct a captured fluid stream into the inlet, through the flow-repositioning duct, and out of the outlet as a buffering fluid stream that flows along the flow-augmented surface. The inlet and the outlet are conformed and/or positioned such that, under the operative conditions, a total pressure at the inlet is greater than a total pressure at the outlet. The methods comprise flowing a bulk fluid stream across the fluid-dynamic exterior, establishing a pressure differential between the inlet and the outlet, and directing the captured fluid stream into the inlet and out of the outlet to flow along the flow-augmented surface as the buffering fluid stream.

Abstract: An aircraft includes a fuselage having a tail section and an engine core coupled via an external pylon to the fuselage. The aircraft further includes a boundary layer ingestion (BLI) fan coupled to the tail section of the fuselage and coupled via a shaft to the engine core.

Abstract: An airflow proximate to leading edges of a turbofan nacelle is ejected substantially normal to a fan face of the turbofan, creating suction proximate to the leading edge and mitigating flow separation proximate to the leading edge. One embodiment comprises a turbofan engine that includes a nacelle, a bypass fan, and a recirculation channel. The recirculation channel is disposed within the nacelle and has a recirculation channel inlet downstream of a leading edge of the bypass fan. The recirculation channel has one or more recirculation channel outlets upstream of the bypass fan that are proximate to a leading edge of a nacelle inlet, where the recirculation channel outlets redirect an airflow from the recirculation channel towards an inside edge of the nacelle inlet to mitigate flow separation at the leading edge of the nacelle inlet.

Abstract: An aircraft includes a fuselage having a tail section and an engine core coupled via an external pylon to the fuselage. The aircraft further includes a boundary layer ingestion (BLI) fan coupled to the tail section of the fuselage and coupled via a shaft to the engine core.

Abstract: A system and methods for deployment operations from an airborne vehicle are presented. A designated location of a target is received at a flight control system coupled to a location tracking guided container comprising an agent. The location tracking guided container is ejected at an ejection point from the airborne vehicle approximately above the designated location of the target to descend at a descent rate and a descent angle. A calculated path to the designated location is calculated based on the designated location and a current location of the location tracking guided container. The location tracking guided container is aerodynamically guided by a glide control structure to fly along the calculated path from the ejection point to a load release altitude near the designated location of the target. The agent is delivered to the designated location of the target by releasing the agent at the load release altitude near the designated location.

Abstract: Apparatus and methods provide for a wing strut having a trailing edge device that is selectively deployable to create aerodynamic lift. Aspects of the disclosure provide a wing strut that is attached to an aircraft fuselage at one end and the aircraft wing at the opposite end. A trailing edge device is attached to the trailing edge of the wing strut. According to various embodiments, the trailing edge device may taper from a maximum chord length at the fuselage, to a minimum chord length near the wing attachment location in order to minimize the effect of the strut on the airflow around the wing. For the same reason, one aspect provides for a change in camber of the wing strut and trailing edge device from a substantially symmetric airfoil at the fuselage to a negatively cambered airfoil near the wing.

Abstract: A system and apparatus for controlling the delivery of fluid from a reservoir, in relation to the ground speed of the vehicle delivering the fluid. Including a system where a hydraulic pump and motor are the components to drive the delivery of the fluid from the reservoir. The hydraulic motor is controlled to vary the output of the fluid pump based on a programmable logic controller (PLC) program. Where an operator selects the desired density of fluid to be pumped, the PLC controls fluid pump flow by controlling the hydraulic motor speed based on the vehicle ground speed.

Abstract: A system and apparatus for controlling the delivery of fluid from a reservoir, in relation to the ground speed of the vehicle delivering the fluid. Including a system where a hydraulic pump and motor are the components to drive the delivery of the fluid from the reservoir. The hydraulic motor is controlled to vary the output of the fluid pump based on a programmable logic controller (PLC) program.

Abstract: An apparatus for retrieving an airborne object has a first hook having an inner area, wherein the first hook is connected to a forward end of the object. A biased member is connected to an open end of the first hook and is biased in a position that substantially closes off the inner area of the first hook. A second hook having an inner area is connected to the first hook. A biased member is connected to the open end of the second hook and is biased in a position that substantially closes off the inner area of the second hook. The first and second hooks are configured to receive one or more grid elements of a flexible grid through a retraction of the biased members when the airborne object is flown into the flexible grid.