A method of managing the propulsion power of an aircraft, the aircraft extending longitudinally along an axis X from back to front and comprising at least two lateral propulsion systems (2) each comprising a blower, each lateral propulsion system having an N2 fan rotation speed and at least one rear propulsion system (3) configured to ingest a boundary layer of said aircraft, the rear propulsion system (3) comprising a fan having an N3 fan rotation speed, the management method comprising, during a cruise phase P4, a step of adjusting the rotation speed N3 of the rear propulsion system (3) according to the following formula N3 = a * N2 in which a is a constant.
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机译：一种管理飞机的推进力的方法，该飞机沿轴线X从后到前纵向延伸，并包括至少两个侧向推进系统（2），每个系统包括一个鼓风机，每个侧向推进系统的风扇转速为N2，至少一个配置成摄取所述飞机边界层的后推进系统（3），该后推进系统（3）包括风扇转速为N3的风扇，该管理方法包括在巡航阶段P4进行以下操作：根据下式，调整后推进系统（3）的转速N3 N3 ＝ a * N2，其中a为常数。
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