A method, apparatus, and system for managing airflow comprising flow control actuators in an aircraft. The flow control actuators comprise channels having inlets and outlets, wherein the channels are located under a surface of the aircraft and the outlets are in communication with the surface of the aircraft. Pressurized air applied to the inlets causes steady air jets to be emitted at the outlets in which the steady air jets add a momentum to airflow over the surface on the aircraft.

A method, apparatus, and system for managing airflow comprising flow control actuators in an aircraft. The flow control actuators comprise channels having inlets and outlets, wherein the channels are located under a surface of the aircraft and the outlets are in communication with the surface of the aircraft. Pressurized air applied to the inlets causes steady air jets to be emitted at the outlets in which the steady air jets add a momentum to airflow over the surface on the aircraft.

Active fluid control systems and related methods are disclosed. A disclosed example active fluid control system includes a plurality of plenums coupled together to define a fluid flow passageway, and a plurality of fluidic actuators coupled to outer surfaces of respective ones of the plenums. The fluidic actuators define actuator inlets and actuator outlets. The fluid flow passageway defined by the plenums to fluidly couple the fluidic actuators and a pressurized fluid supply source. The plenums are configured to couple to an aircraft structure supporting an aerodynamic surface to enable the actuator outlets to be mounted to the aerodynamic surface. The fluidic actuators are configured to provide the pressurized fluid to the aerodynamic surface to modify an aerodynamic characteristic of the aerodynamic surface.

Active fluid control systems and related methods are disclosed. A disclosed example active fluid control system includes a plurality of plenums coupled together to define a fluid flow passageway, and a plurality of fluidic actuators coupled to outer surfaces of respective ones of the plenums. The fluidic actuators define actuator inlets and actuator outlets. The fluid flow passageway defined by the plenums to fluidly couple the fluidic actuators and a pressurized fluid supply source. The plenums are configured to couple to an aircraft structure supporting an aerodynamic surface to enable the actuator outlets to be mounted to the aerodynamic surface. The fluidic actuators are configured to provide the pressurized fluid to the aerodynamic surface to modify an aerodynamic characteristic of the aerodynamic surface.

A ducted fan assembly for generating thrust during edgewise forward flight. The ducted fan assembly includes a duct having an inlet with a leading portion and a diffuser with a trailing portion during the edgewise forward flight. A fan disposed within the duct is configured to rotate relative to the duct about a fan axis to generate an airflow through the duct from the inlet to the diffuser. An active flow control system includes a plurality of injectors including a first injector configured to inject pressurized air substantially tangential with the leading portion of the inlet and a second injector configured to inject pressurized air substantially tangential with the trailing portion of the diffuser such that when the injectors are injecting pressurized air, flow separation of the airflow at the leading portion of the inlet and the trailing portion of the diffuser is reduced.

A ducted fan assembly for generating thrust during edgewise forward flight. The ducted fan assembly includes a duct having an inlet with a leading portion and a diffuser with a trailing portion during the edgewise forward flight. A fan disposed within the duct is configured to rotate relative to the duct about a fan axis to generate an airflow through the duct from the inlet to the diffuser. An active flow control system includes a plurality of injectors including a first injector configured to inject pressurized air substantially tangential with the leading portion of the inlet and a second injector configured to inject pressurized air substantially tangential with the trailing portion of the diffuser such that when the injectors are injecting pressurized air, flow separation of the airflow at the leading portion of the inlet and the trailing portion of the diffuser is reduced.

The aircraft can have a first engine secured to a first wing on a first side of a fuselage, and a second engine secured to a second wing on a second side of the fuselage, the second wing having a proximal end secured to the fuselage, and a distal end extending away from the fuselage. While operating the first engine, compressed gas can be conveyed from the first engine to a thrust generating device located at the distal end of the second wing.

An aircraft having an airframe with several airframe elements and at least one fluidic propulsion device with a peripheral nozzle defining an internal cavity in which an external airflow circulates, the peripheral nozzle having openings configured to inject a plurality of high-speed airflows into the internal cavity so as to accelerate the external airflow in an upstream to downstream manner. A portion of the peripheral nozzle can be integrated into an airframe element so as to enable acceleration of an external airflow circulating from upstream to downstream on said airframe element so as to improve its re-adhesion to said airframe element.

Example active flow control systems and methods for aircraft are described herein. An example an active flow control system includes a plenum, a plurality of nozzles fluidly coupled to the plenum, configured to eject high pressure air across a control surface, a compressor to supply pressurized air to the plenum, an electric motor to drive the compressor, and a control system to determine an amount of power input to the electric motor, determine a current speed of the electric motor, and determine a fault has occurred in the active flow control system based on the current speed of the electric motor.

Example active flow control systems and methods for aircraft are described herein. An example an active flow control system includes a plenum, a plurality of nozzles fluidly coupled to the plenum, configured to eject high pressure air across a control surface, a compressor to supply pressurized air to the plenum, an electric motor to drive the compressor, and a control system to determine an amount of power input to the electric motor, determine a current speed of the electric motor, and determine a fault has occurred in the active flow control system based on the current speed of the electric motor.