NACELLE DRAG REDUCTION DEVICE FOR A TURBOFAN GAS TURBINE ENGINE

摘要

The nacelle drag reduction device (22) comprises a substantially circular and axis symmetrical external airfoil (24) concentric with a aft section of the nacelle (20) and located outside a propulsive jet zone (30) defined beh ind the engine (10) when operating, the airfoil (24) being positioned at a l ocation providing a maximum streamline angle with reference to the main axis (26) of the engine (10) and a highest streamline curvature.