|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/130 ; 244/53R ; 244/35R|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 15 인용 특허 : 6|
An improved nacelle is provided for housing an aircraft engine and reducing aerodynamic drag during aircraft operation. In one embodiment, the nacelle houses a gas turbine engine and comprises a leading edge and a trailing edge, having a reference chord extending therebetween, and an outer surface which is continuous from the leading edge to the trailing edge. The outer surface includes a forward portion, an intermediate portion and an aft portion that has a profile defined by a varying thickness measured perpendicularly from the chord to the outer surfa...
A nacelle for use on an aircraft comprising: an annular leading edge and an annular trailing edge having a reference chord of length C extending from said leading edge to said trailing edge and; an outer annular surface continuous from said leading edge to said trailing edge and including a forward portion, an intermediate portion and an aft portion, said outer surface being devoid of aerodynamic drag reducing holes, slots and active devices; said outer surface having a profile defined by a relative thickness measured perpendicularly from said chord to s...