1. A propulsion system for an aircraft (10) having a fuselage (12), the propulsion
system comprising:
an aft engine configured to be mounted to the aircraft (10) at an aft end of the aircraft (10), the aft engine defining a central axis and including
a fan (304) rotatable about the central axis of the aft engine and including a plurality of fan blades (310);
a nacelle (306) encircling the plurality of fan blades (310) of the fan (304) and extending around the mean line (15) of the aircraft (10) at the aft end of the aircraft (10) when the aft engine is mounted to the aircraft (10); and
one or more structural members (308) extending between the nacelle (306) and the fuselage (12) of the aircraft (10) at a location forward of the plurality of fan blades (310) when the aft engine is mounted to the aircraft (10).
2. The propulsion system as claimed in claim 1, wherein the aft engine is configured as a boundary layer ingestion fan (304).
3. The propulsion system as claimed in claim 1, wherein the aft engine further includes a tail cone (340) and one or more outlet guide vanes (338), wherein the one or more outlet guide vanes (338) extend from the nacelle (306) to the tail cone (340).
4. The propulsion system as claimed in claim 1, wherein the fan (304) of the aft engine includes a fan shaft (312), wherein the fan shaft (312) is mechanically coupled to a power source (314) located forward of the plurality of fan blades (310) of the fan (304).
5. The propulsion system as claimed in claim 5, wherein the fan shaft (312) is mechanically coupled to the power source (314) through a gearbox (316).

6. The propulsion system as claimed in claim 1, wherein the fan (304) of the aft engine is configured as a variable pitch fan.
7. The propulsion system as claimed in claim 1, wherein the nacelle (306) defines an inlet (334) extending substantially 360 degrees around the mean line (15) of the aircraft (10) when the aft engine is mounted to the aircraft (10).
8. The propulsion system as claimed in claim 1, wherein the aft engine defines a circumferential direction, and wherein the one or more structural members (308) include a plurality of structural members (308) spaced along the circumferential direction of the aft engine.
9. The propulsion system as claimed in claim 1, wherein the aft engine defines a radial direction, and wherein the one or more structural members (308) include a plurality of structural members (308) extending substantially along the radial direction of the aft engine.
10. The propulsion system as claimed in claim 1, wherein the one or more structural members (308) are configured as variable inlet guide vanes.