|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 32 인용 특허 : 14|
The present invention provides a system and method for controlling leading edge contamination and crossflow instabilities for laminar flow on aircraft airfoils that is lightweight, low power, economical and reliable. Plasma surface discharges supply volumetric heating of the supersonic boundary layers to control the Poll Reynolds number and the cross flow Reynolds number and delay transition to turbulent flow associated with the leading edge contamination and crossflow instabilities. A closed-loop feedback control system that incorporates these principle...
1. An aircraft, comprising:an airfoil having a leading edge, whereby air flow interacts with the leading edge to create a first boundary layer, characterized by a Poll Reynolds number, along an attachment line and a second boundary layer, characterized by a cross flow Reynolds number, along diverging streamlines, andplasma discharge elements distributed along the attachment line, said plasma discharge elements being adapted to generate a plasma to volumetrically heat the first and second boundary layers, thereby maintaining the Poll Reynolds number below...