<p>A diverterless engine inlet system (10) integrates a transition shoulder into a system for diverting air from the inlet of a jet aircraft engine. A bump (20) includes an isentropic compression surface raised outwardly from the body of the aircraft to form a portion of the inner surface of the inlet. The transition surface works with the compression surface to divert low energy boundary layer air from the inlet during aircraft operation. <IMAGE></p>
申请公布号
DE69715303(T2)
申请公布日期
2003.04.17
申请号
DE1997615303T
申请日期
1997.05.19
申请人
LOCKHEED MARTIN CORP., BETHESDA
发明人
HAMSTRA, JEFFREY WILLIAM;MCCALLUM, BRENT NEAL;SYLVESTER, THOMAS GERARD;DENNER, BRETT WILLIAM;MOOREHOUSE, JEFFREY ALLEN