Angled reverse core gas turbine engine with widened nozzle

A propulsion system for an aircraft, comprising:

• a first turbine engine including a first engine core having a first compressor, a first combustor, a first turbine, and a first intake duct leading into the first compressor;
• a second turbine engine including a second engine core having a second compressor, a second combustor, a second turbine, and a second intake duct leading into the second compressor;
• a first propulsor coupled to be driven by the first turbine engine, the first propulsor being disposed about a first propulsor axis and the first engine core being disposed about a first core axis that is skewed from the first propulsor axis;
• a second propulsor coupled to be driven by the second turbine engine, the second propulsor being disposed about a second propulsor axis parallel to the first propulsor axis, and the second engine core being disposed about a second core axis that is skewed from the second propulsor axis;
• and
• a furcated nozzle having at least a first duct extending from the first propulsor to a first trailing end duct opening and a second duct extending from the second propulsor to a second trailing end duct opening, wherein the first trailing end duct opening and the second trailing end duct opening are each laterally elongated.