|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 1 인용 특허 : 85|
A supersonic inlet with a cowl lip may be configured to capture the conic shock and exhibit a zero or substantially zero cowl angle. The inlet may be configured to employ a relaxed isentropic compression surface and an internal bypass. The nacelle bypass may prevent flow distortions, introduced by the capture of the conic shock, from reaching the turbomachinery, thereby allowing the cowl angle to be reduced to zero or substantially zero. Such a cowl angle may reduce the inlet's contribution to the overall sonic boom signature for a supersonic aircraft wh...
1. A supersonic inlet: comprising: a center body having a leading edge that generates a first shock wave when positioned in supersonic air flow, the center body comprising a compression surface positioned downstream from the leading edge of the center body;a cowl lip spatially separated from the center body such that the cowl lip and the compression surface of the center body define an external compression inlet opening that receives supersonic air flow, at least a portion of the compression surface extending upstream of the cowl lip, and the cowl lip be...