Systems and methods capable for use in the development of high-speed, shape-transitioning, inward-turning inlets for air-breathing hypersonic vehicles, and inlets formed thereby. The systems and methods preferably provide for designing high-speed inlets for air-breathing hypersonic vehicles, wherein unique solutions are defined in each osculating plane of the inlet. Such systems and methods optionally provide an optimization process for tuning the post throat-shock Mach number of the inlet, and/or designs a shock-capture surface using a parallel-streamlines methodology, and/or a double cowl-lip geometry to allow flow to spill overboard.

The present invention discloses an internal-parallel inlet with mode conversion combined with variable geometry adjustment, which comprises a high-speed channel, a low-speed channel, a mode conversion component, a variable geometry component and a motor actuating component. When the inlet is in a low-speed mode, the variable geometry component adjusts the throat area and the internal contraction ratio of the inlet. When the flight Mach number is in a range of the mode conversion Mach number, the mode conversion component and the variable geometry component work simultaneously. When the inlet is in a high-speed mode, the mode conversion component is combined with the variable geometry component to adjust the throat area and the internal contraction ratio of the inlet. The present invention also provides a method for controlling the inlet.

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 engine inlet for efficient operation at both design Mach number and off-design Mach numbers with an inlet having a caret configuration with rotatably extending effective leading edges on the inlet from a retracted position aligned with a nominal Mach number shock wave to an extended position aligned with an off-design Mach number shock wave.

Systems and methods capable for use in the development of high-speed, shape-transitioning, inward-turning inlets for air-breathing hypersonic vehicles, and inlets formed thereby. The systems and methods preferably provide for designing high-speed inlets for air-breathing hypersonic vehicles, wherein unique solutions are defined in each osculating plane of the inlet. Such systems and methods optionally provide an optimization process for tuning the post throat-shock Mach number of the inlet, and/or designs a shock-capture surface using a parallel-streamlines methodology, and/or a double cowl-lip geometry to allow flow to spill overboard.

An engine inlet for efficient operation at both design Mach number and off-design Mach numbers has a fixed compression surface and a leading edge that is variably extendible over the fixed compression surface to simultaneously vary capture area, compression and shock wave position.

An apparatus is formed of a cowl and a flow inlet formed on an interior surface of the cowl. The flow inlet has a supersonic compression section attached to a subsonic diffusion section at a throat. The supersonic compression section includes an at least partially elliptical compression ramp which extends along an approximately 180 degree arc along the interior surface. The flow inlet may form part of an aircraft. A method of air flow using the flow inlet is also disclosed.

A propulsion system for a supersonic aircraft includes an engine including an engine core and an engine bypass, a compression surface upstream of the engine, a shroud surrounding the engine configured to direct airflow passing over the compression surface towards the engine, and a plurality of vortex generators positioned upstream of the engine. The vortex generators have a height such that when the supersonic aircraft is flown at a predetermined altitude and predetermined speed, the plurality of vortex generators create vortices that propagate partially outside of a boundary layer formed proximate a surface of a supersonic inlet. The vortices cause a high-velocity portion of the airflow to move towards the engine core and a low-velocity portion of the airflow to move towards the engine bypass. The plurality of vortex generators are disposed aft of a terminal shock and have a height greater than the thickness of the boundary layer.

An engine inlet for efficient operation in both subsonic and supersonic flight wherein the inlet has a caret configuration is rotatable about an off-body axis for compression ramp angle and capture area variation and a diffuser is engaged to the inlet in a scrubbing relationship to maintain a seal upon rotation of the inlet.

A high-speed propulsion system for a high-speed vehicle includes an air intake duct, a compression section, a combustion section, and an expansion section. A gas dynamic laser generator is disposed proximate the expansion section and generates a source of laser light. A laser transmission mechanism receives the laser light and transmits the laser light from the gas dynamic laser generator to the combustion section and to presents the laser light into the air/fuel mixture of the flowpath which promotes mixing, combustion, and flame stability.