| 摘要 |
<p>An apparatus and a method for reducing drag over an aircraft wing assembly in operational angle of attack situations are disclosed. The aircraft wing assembly (200) includes a wing (210) and an engine nacelle (220) mounted to the wing. A nacelle chine (250) is mounted on an outboard side of the engine nacelle (220), and the nacelle chine (250) is configured to reduce drag by redirecting at least a portion of fluid striking a forward end of the aircraft wing assembly (200) such that a vortex (290) is formed over the forward end of the aircraft wing assembly (200). The chine (250) is coupled to a mounting base (260) configured to be secured to an outer surface of the engine nacelle (220) at a mounting position along an outer surface of the engine nacelle (220).</p> |
