Fluid systems are described herein. An example embodiment of a fluid system has a lengthwise axis, a chord length, a first body portion, a second body portion, a spacer, and a fluid pressurizer. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. The first body portion defines a cavity that is sized and configured to filter debris that enters the channel during use and provide a mechanism for removing the debris from the system.

Fluid systems are described herein. An example embodiment of a fluid system has a lengthwise axis, a chord length, a first body portion, a second body portion, a spacer, and a fluid pressurizer. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. The first body portion defines a cavity that is sized and configured to filter debris that enters the channel during use and provide a mechanism for removing the debris from the system.

A fairing assembly is provided about a duct outlet port, which is not parallel to an exterior surface of a vehicle, so as to turn fluid flow exiting the duct outlet port in a direction of surface fluid flow. The fairing assembly includes an upstream vane fairing to orient the surface flow with the angled duct flow, a downstream Coanda fairing to turn transverse duct flow in the direction of the surface flow, and a pair of vortex generators each of which is positioned at an opposing lateral side of the Coanda fairing and angled towards each other to organize the combined fluid flow downstream of the duct outlet port to thereby minimize recirculation. This fairing assembly about the duct outlet port enhances organized mixing of the duct and surface flows, and thereby reduces duct and surface recirculation, duct restriction, and overall vehicle drag.

A fairing assembly is provided about a duct outlet port, which is not parallel to an exterior surface of a vehicle, so as to turn fluid flow exiting the duct outlet port in a direction of surface fluid flow. The fairing assembly includes an upstream vane fairing to orient the surface flow with the angled duct flow, a downstream Coanda fairing to turn transverse duct flow in the direction of the surface flow, and a pair of vortex generators each of which is positioned at an opposing lateral side of the Coanda fairing and angled towards each other to organize the combined fluid flow downstream of the duct outlet port to thereby minimize recirculation. This fairing assembly about the duct outlet port enhances organized mixing of the duct and surface flows, and thereby reduces duct and surface recirculation, duct restriction, and overall vehicle drag.

A removable passive airflow oscillation device can be disposed within a pressurized wing structure utilized as a plenum. The passive airflow oscillation device can be a removable insert disposed into exterior vehicle surfaces with pressurization of a sealed chamber to provide the airflow. The device can include a cavity configured to receive the airflow from an ingress opening, direct the airflow therethrough to generate a predetermined oscillating airflow, and expel the oscillatory airflow from the egress opening. The removable passive airflow oscillation devices can provide quick and simple replacement and maintenance of damaged or clogged devices. The aft chamber of the flap seal can be sealed and pressurized to serve as a plenum providing the airflow to the actuators. The device can receive airflow, such as compressor air, and expel an oscillating airflow. Because each device is self-contained the number of devices and location thereof can vary by application.

A leading edge structure for a flow control system of an aircraft is disclosed having a leading edge panel that surrounds a plenum, wherein the leading edge panel has a first side portion, a second side portion opposite the first side portion, an inner surface facing the plenum and an outer surface in contact with an ambient flow, and wherein the leading edge panel comprises a plurality of micro pores forming a fluid connection between the plenum and the ambient flow, wherein the plenum is connected to an air outlet arrangement configured for causing an underpressure in the plenum, so that air from the ambient flow is drawn through the micro pores into the plenum and from there discharged through the air outlet arrangement into the ambient flow.

An aircraft including a fuselage with one or more wings extending from the fuselage. The aircraft may include one or more apertures in a surface of at least one of the fuselage and the one or more wings. The one or more apertures may be configured to enable air to pass through the one or more apertures when the aircraft is flying.

An aircraft including a fuselage with one or more wings extending from the fuselage. The aircraft may include one or more apertures in a surface of at least one of the fuselage and the one or more wings. The one or more apertures may be configured to enable air to pass through the one or more apertures when the aircraft is flying.

A wing structure for a supersonic aircraft including a pair of supersonic wave-tripping channels formed on each of two laterally extending wings of the supersonic aircraft, wherein each of the pair of supersonic wave-tripping channels extend in a span-wise direction of the wings respectively, wherein an upper supersonic wave-tripping channel of the pair of supersonic wave-tripping channels is disposed on an upper surface of each of the wings and a lower supersonic wave-tripping channel of the pair of supersonic wave-tripping channels is disposed on a lower surface of each of the wings, wherein the upper supersonic wave-tripping channel and the lower supersonic wave-tripping channel are set back from a leading edge of the wings respectively.

Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.