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发明公开
CN108116663A 具有基于边界层吸入式风扇的阻力补偿装置的飞行器 无效 - 撤回

具有基于边界层吸入式风扇的阻力补偿装置的飞行器
摘要：
本发明提出了一种飞行器(2)，该飞行器包括：具有渐缩的后部形状的机身、用于使飞行器(2)在跑道上移动的起落架、附接至机身的机翼、用于提供主推力的至少一个主发动机以及后部风扇(14)，其中，后部风扇(14)附接至机身的尾部部段，其中，飞行器(2)设计成用于在从跑道起飞期间执行围绕起落架的起飞旋转，使得机身的尾部部段靠近跑道，其中，后部风扇(14)是具有风扇叶片(36)的敞开式风扇，风扇叶片(36)沿径向方向延伸至机身的纵向轴线，其中，风扇叶片(36)定尺寸成至少等于沿着机身的流的边界层的厚度且小于跑道与机身的尾部部段之间在起飞旋转期间的间隙。
摘要（英）：

An aircraft (2) is proposed, comprising a fuselage having a tapered rear shape, a landing gear for moving the aircraft (2) on a runway, a wing attached to the fuselage, at least a main engine for providing a main thrust and a rear fan (14), wherein the rear fan (14) is attached to a tail section of the fuselage, the aircraft (2) is designed for conducting a take-off rotation around the landing gear during take-off from the runway, such that the tail section of the fuselage approaches the runway, the rear fan (14) is an open fan having fan blades (36) extending in a radial direction to a longitudinal axis of the fuselage, and the fan blades (36) are dimensioned to equal at least a boundary layer thickness of the flow along the fuselage and to be smaller than the gap between the runway and the tail section of the fuselage during the take-off rotation.

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