Aircraft propulsion system with variable area inlet assembly

An assembly for an aircraft propulsion system, comprising:

• a center body comprising a center body surface with a trailing edge;
• a nacelle inlet structure extending circumferentially around the center body, the nacelle inlet structure having a leading edge;
• an inlet passage radially between and formed by at least the center body and the nacelle inlet structure, the inlet passage comprising a metering portion;
• and
• a turbine engine comprising a plurality of flowpaths fluidly coupled in parallel to and downstream of the inlet passage;
• a first component of the assembly configured to rotate about a rotational axis of the first component of the assembly relative to a second component of the assembly between
• a first position where the metering portion has a first area, and where the trailing edge is axially displaced from the leading edge by a first distance;
• and
• a second position where the metering portion has a second area that is different than the first area, and where the trailing edge is axially displaced from the leading edge by a second distance that is different than the first distance;
• the first component of the assembly comprising one of the center body or the nacelle inlet structure;
• and
• the second component of the assembly comprising the other one of the center body or the nacelle inlet structure, and the rotational axis offset from a centerline of the turbine engine.