| 摘要 |
This invention relates to an aircraft comprising: a first propulsive unit (12) having a first fan (30) with an axis of rotation (22); and a second propulsive unit (14) local to the first propulsive unit, the second propulsive unit having a second fan (52) with an axis of rotation (42), wherein the rotational axis (22) of the first fan (30) is proximate to the surface of the aircraft (50) relative to the rotational axis (42) of the second fan (52) such that the first fan ingests boundary layer air when in use. |
