Abstract: 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.

Abstract: A propulsion system for an aircraft is taught herein. The propulsion system includes, but is not limited to, an engine that is configured to produce a gas jet. The propulsion system further includes a nozzle that is coupled with the engine and that is disposed to receive the gas jet. The nozzle has a throat that is configured to expand and contract. The propulsion system still further includes a controller that is operatively coupled with the throat. The controller is configured to control the throat to expand and contract and to control a magnitude of a thrust imparted by the gas jet by controlling the throat to expand and contract. The controller is further configured to control the magnitude of the thrust by controlling the throat to expand and contract when the aircraft is flying at or above the local speed of sound.

Abstract: 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.

Abstract: 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.

Abstract: A propulsion system for a supersonic aircraft includes an engine, 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 speed, the plurality of vortex generators create a plurality of 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 a portion of the engine having a higher sensitivity to changes in stagnation pressure and a low-velocity portion of the airflow to move away from the portion of the engine having the higher sensitivity to changes in stagnation pressure prior to the airflow reaching a face of the engine.