|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 20 인용 특허 : 0|
An inlet duct of generally rectangular configuration for supersonic aircraft in which a normal shock is produced in close proximity to the forward lip of the lower duct wall, and in which variable area sideplate openings are provided just upstream of the normal shock to achieve boundary layer control for the normal shock-boundary layer interaction during on-design operation and increasing flow area for spillage as the normal shock is moved forward during off-design operation.
An inlet duct for supersonic aircraft comprising an inlet channel having top and bottom walls and side walls, the top wall extending beyond the forward lip of the bottom wall and the lower edges of the side walls extending from the forward lip of the top wall to the forward lip of the bottom wall, the walls of the duct being arranged to produce a normal shock wave in close proximity to said forward lip of the bottom wall, variable area slot means located through said side walls upstream of said bottom wall forward lip and, during substantially all engine...