A system and a method for reducing drag on the aft-fuselage of an aircraft are provided, which system and method utilize at least one (inlet provided on each side of the aft-fuselage of an aircraft for reducing drag -on the aft-fuselage, which finlets are (i) positioned at the rear half of an upswept portion of the aft-fuselage starting at a breakline, (ii) positioned in the path of the vortices generated by the aft-fuselage, and (iii) oriented at 1 to 9 degrees angle relative to the local airflow about the aft-fuselage of the aircraft to straighten the airflow about the aft-fuselage. In addition, the finlets generate an induced secondary vortex having an opposite rotation direction relative to the rotation direction of the vortices generated by the aft-fuselage, thereby counteracting the vortices generated by the aft-fuselage.
FINLETS FOR AIRCRAFT AFT-BODY DRAG REDUCTION
2019-11-14
Patent
Electronic Resource
English
AIAA | 1993
|Online Contents | 1994
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