Aircraft propulsion system with core flowpath inlet forward of fan rotor

An aircraft system, comprising:

• a propulsion system extending axially along an axis from a forward end of the propulsion system to an aft end of the propulsion system, the propulsion system including a fan rotor, an engine core, an outer housing structure, an inner housing structure, an inlet flowpath, a bypass flowpath and a core flowpath;
• the fan rotor configured to propel air through the bypass flowpath;
• the engine core configured to drive rotation of the fan rotor about the axis, and the engine core including a compressor section, a combustor section and a turbine section;
• the outer housing structure housing the fan rotor, and the outer housing structure disposed radially outboard of and extending axially along the inlet flowpath and the bypass flowpath;
• the inner housing structure housing the engine core, and the inner housing structure disposed radially inboard of and extending axially along the bypass flowpath;
• the inlet flowpath projecting longitudinally into the propulsion system from an airflow inlet into the propulsion system, and the inlet flowpath fluidly coupled with and upstream of the bypass flowpath and the core flowpath;
• and
• the core flowpath including a core inlet and a core exhaust, the core flowpath extending longitudinally through the compressor section, the combustor section and the turbine section from the core inlet to the core exhaust, and the core inlet located axially forward of the fan rotor.