Abstract: 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 includes a wing and an engine nacelle mounted to the wing. A nacelle chine is mounted on an outboard side of the engine nacelle, and the nacelle chine is configured to reduce drag by redirecting at least a portion of fluid striking a forward end of the aircraft wing assembly such that a vortex is formed over the forward end of the aircraft wing assembly. The chine is coupled to a mounting base configured to be secured to an outer surface of the engine nacelle at a mounting position along an outer surface of the engine nacelle.