|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/117A ; 244/209 ; 60/267|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 6 인용 특허 : 2|
The invention comprises a combination boundary layer control system that utilizes both suction and cryogenic wall cooling to reduce aircraft drag. The invention is particulary useful in circumstances where liquid hydrogen or other cryogenic fuels are used to operate the aircraft. In the preferred embodiment of the invention, a network of D-tube ducts are provided that are fluidly connected to a cryogenic fluid source. These cryogenic fluid ducts are selectively fed cryogenic fluid to reduce aircraft surrface temperature and promote adhesion of boundary l...
A combination boundary layer control system for high altitude aircraft comprising: a cryogenic cooling system for directing a cryogenic fluid into intimate contact with an aircraft surface in order to lower the aircraft surface temperature to less than 100°F. and thus promote boundary layer adhesion; and an air duct system for applying suction to the aircraft surface in order to prevent boundary layer separation.