|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64C-021/04 B64C-009/38 B64C-009/16 B64C-003/18 B64C-009/00|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 0 인용 특허 : 7|
A drag reduction system for an aircraft may include an air ejector having an ejection port located between an aft portion of an airfoil main element and a forward portion of a trailing edge device. The air ejector may be configured to discharge an air jet from the ejection port in such a manner that the air jet passes over the upper surface of the trailing edge device.
1. A drag reduction system for an airfoil, comprising: an air ejector having an ejection port mounted on or extending aftwardly from an aft portion of an airfoil main element of the airfoil, the ejection port terminating within a main cove having side boundaries defined by the aft portion of the airfoil main element and a forward portion of a trailing edge device and an upper boundary defined by an overhang extending from the aft portion of the airfoil main element, the election port terminating at a location below the overhang; andthe air ejector config...