An inlet concept for separate turbojet and ramjet engines was defined and compared with an equivalent inlet for a wraparound turboramjet engine. The comparison was made for a typical high altitude hypersonic cruise vehicle where the turbojet inlet capture area was required to be half as large as the ramjet inlet capture area at cruise. The use of a shorter nacelle having substantially lower cooling requirements at cruise for the inlet concept for separate turbojet and ramjet engines is suggested. The separate engine concept better isolates the turbojet from the ramjet, requires no special close off mechanisms within the turbojet, and avoids the circumferential heat load imposed by a wraparound ramjet. A more variable geometry is required.
Conceptual study of a turbojet/ramjet inlet
1979-09-01
Report
No indication
English
Conceptual Study of a Turbojet/Ramjet Inlet
NTIS | 1979
|Conceptual study of a turbojet/ramjet inlet
TIBKAT | 1979
|Ramjet-Turbojet propulsion system for supersonic flight
Engineering Index Backfile | 1957
|Ramjet-Turbojet propulsion system for supersonic flight
Engineering Index Backfile | 1957
|Hydrogen for Turbojet and Ramjet Powered Flight
NTRS | 1957