검색연산자 | 기능 | 검색시 예 |
---|---|---|
() | 우선순위가 가장 높은 연산자 | 예1) (나노 (기계 | machine)) |
공백 | 두 개의 검색어(식)을 모두 포함하고 있는 문서 검색 | 예1) (나노 기계) 예2) 나노 장영실 |
| | 두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색 | 예1) (줄기세포 | 면역) 예2) 줄기세포 | 장영실 |
! | NOT 이후에 있는 검색어가 포함된 문서는 제외 | 예1) (황금 !백금) 예2) !image |
* | 검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색 | 예) semi* |
"" | 따옴표 내의 구문과 완전히 일치하는 문서만 검색 | 예) "Transform and Quantization" |
국가/구분 | United States(US) Patent 등록 |
---|---|
국제특허분류(IPC7판) | B64C-005/08 |
미국특허분류(USC) | 244/199 ; 244/91 |
출원번호 | US-0797788 (1977-05-17) |
발명자 / 주소 | |
출원인 / 주소 | |
인용정보 | 피인용 횟수 : 37 인용 특허 : 0 |
The vortex system behind an aircraft is responsible for more than half of the aircraft drag in cruise flight and sometimes more in other flight conditions. The purpose of the vortex diffuser is to intercept the wing tip vortex just aft of the wing trailing edge, diffuse the trailing vorticity and thereby achieve a reduction in drag. To do this, an airfoil-shaped device is mounted on a trailing boom situated at or near to the wing tip. The airfoil is mounted above the boom at an angle inboard of the vertical. Its height is a percentage of wing semispan as...
A vortex diffuser to attenuate vortex flow after its formation and emanation from an airplane wing, such diffuser consisting of an aerodynamically configured boom secured to and extending aftwardly from said wing adjacent the outer tip thereof, and a single asymmetric vane secured to one side of said boom adjacent the aft end thereof and located entirely aft of said wing, said vane extending upward from said one side of said boom in a generally vertical direction and disposed in the path of said vortex flow, being cambered toward its leading edge so as t...