Propulsion system for an aircraft

A propulsion system for use with an aircraft, the propulsion system comprising:

• an engine having a predetermined tolerance for flow distortion;
• an inlet disposed upstream of the engine, the inlet including a forward cowl lip and an aft cowl lip, the forward cowl lip disposed forward of the aft cowl lip, the forward cowl lip configured to move between a retracted position and a deployed position, the forward cowl lip being adjacent to the aft cowl lip in a fluid tight arrangement such that a freestream of air is precluded from passing between the forward cowl lip and the aft cowl lip when the forward cowl lip is in the retracted position, the forward cowl lip being spaced apart from the aft cowl lip such that the freestream of air can flow between the forward cowl lip and the aft cowl lip when the forward cowl lip is in the deployed position, the forward cowl lip having a first radius of curvature, the aft cowl lip having a second radius of curvature, the first radius of curvature being less than or equal to the second radius of curvature;
• a nozzle assembly disposed downstream of the engine, the nozzle assembly having a variable nozzle throat, the variable nozzle throat configured to expand and contract between a maximum open state and a minimum open state;
• and
• a controller operatively coupled with the engine, with the inlet, and with the nozzle assembly, the controller configured to impose a restriction on a maximum thrust commanded position of the engine when the aircraft is on a ground surface and moving below a predetermined speed, the controller further configured to lift the restriction when the aircraft is moving at at least the predetermined speed, the controller is further configured to control the inlet to extend the forward cowl lip to the deployed position when the aircraft is on the ground surface and wherein the controller is still further configured to control the nozzle assembly to expand the variable nozzle throat to an extent that will maintain a mass flow passing through the nozzle assembly below a choked condition when the aircraft is on the ground surface and the engine is delivering the maximum power and the forward cowl lip is extended to the deployed position.