An arrangement for use with a propulsion system for a supersonic aircraft includes a center body configured for coupling to an inlet and to support a boundary layer formed when the supersonic aircraft is flown at a predetermined altitude supersonic speed. The arrangement further includes a first vortex generator disposed on the center body. The first vortex generator extends a first height above the center body. The arrangement still further includes a second vortex generator disposed on the center body. The second vortex generator extends a second height above the center body, the second height being greater than the first height. The first height and the second height are greater than approximately seventy-five percent of a thickness of the boundary layer proximate a location of the first vortex generator and the second vortex generator, respectively, when the aircraft if flown at the predetermined altitude and the predetermined speed.

An aircraft defines a longitudinal direction and includes a fuselage extending between a forward end and an aft end along the longitudinal direction of the aircraft. An aft engine is mounted to the aft end of the fuselage. The aft engine further includes a nacelle including a forward section. An airflow duct extends at least partially through the nacelle of the aft engine and defines an outlet on the forward section of the nacelle for providing an airflow to the forward section of the nacelle.

A method and apparatus are presented. An active flow control system comprises a flow control valve, a manifold, and a temperature control system. The flow control valve is configured to control a flow of air into the manifold. The manifold is operatively connected to a number of actuators. The temperature control system is configured to heat at least a portion of the flow of air.

An engine nacelle is provided for an aircraft. The engine nacelle comprises: an inlet for receiving an air flow to generate a thrust force for the aircraft; a lip portion positioned at the inlet and surrounding the inlet; and at least one strake provided on a surface of the engine nacelle.

A rotorcraft has a fuselage, an engine disposed substantially laterally centrally relative to the fuselage, and an air intake system (AIS). The AIS has a first duct configured to provide streamline air flow, a second duct configured to provide streamline air flow, and a combining section configured to receive streamline air flow from each of the first duct and the second duct. The combining section is further configured to output streamline air flow.

A vehicle includes a main body and at least one wing coupled to the main body. A source of compressed fluid is coupled to the main body. The vehicle further includes first and second thrusters, each said first and second thruster having an intake structure and each said first and second thruster in fluid communication with the source. The first thruster is coupled to the main body and the second thruster is coupled to the at least one wing. The first and second thrusters are positioned, when in a first configuration, such that at least a portion of a boundary layer produced due to motion of the vehicle is ingested by the intake structures of the first and second thrusters. The vehicle further includes a system for selectively providing the compressed fluid to the first and second thrusters.

An element including a leading edge forming a box delimited by a skin forming a lower surface and an upper surface and pierced with holes, in which the skin includes an inner wall and an outer wall that are electrically conductive and an electrically insulating intermediate wall, a pump for expelling or injecting air from or into the box. Each hole is equipped with an anti-clogging system including a conductive base, a needle made of piezoelectric material, one end of which is secured to the base, an electrical generator generating an electrical current in the needle, in which the form of the needle is such that a space is created between the needle and the edges of the hole, and in which the base has a recess in the extension of the space. Such an installation makes it possible to eliminate the residues which are lodged in the holes.

An inlet for a flight vehicle engine, such as for a supersonic or hypersonic engine, includes an internal flow diverter to divert boundary layer flow. The flow diverter is configured to minimize disruption to flow outside the diverted boundary by being configured through use of a flow field that is also used to configure the walls of the inlet. The flow field that is used to configure an inlet-creating shape and a diverter-creating shape has the same flow generator, contraction ratio, compression ratio, mass capture ratio, pressure ratio between entrance and exit, and/or Mach number, for example. The internal diverter may be configured so as to allow arbitrary selection of a leading edge shape for the internal diverter, for example to use a shape that helps avoid radar detection.

A method of operating a turbofan engine includes coupling an electric motor to drive a fan rotatable within a nacelle, detecting an in-flight operating condition indicative of an increase in drag, and driving rotation of the fan with the electric motor to redirect a flow of air through the nacelle to reduce drag. A turbofan engine is also disclosed.

A wing comprising a leading edge forming a caisson delimited by a wall and an electrically conductive skin forming a lower surface and an upper surface and pierced with holes. A pump is provided to suck the air present in the caisson and/or to inject air into the caisson. The wing includes a voltage generator. Each hole is equipped with an anti-clogging system which comprises an electrically conductive electrode, an electrically insulating body having a stem which lodges in the hole and which has a central orifice in which the electrode lodges. The outer face of the stem has at least one tooth, where each tooth protrudes from the outer face of the stem and extends over the height of the stem. The at least one tooth is distributed around the stem so as to create at least one channel.