Description of L-2000 SST as developed at end of Phase II-A featuring large fixed wing of double-delta configuration, vertical fin, and no horizontal tail; four jet engines are located in independent nacelles on lower surface of wing, with exhaust nozzles at trailing edge; operating environment and typical flight profile; airframe arrangement; crew and payload accommodations; structure uses titanium alloy as basic material; duplex-annealed Ti 8Al-1Mo-1V is predominant alloy; Ti 6Al-4V is used in power plant area where temperatures exceed 500 F; wing, fuselage, and landing gear; propulsion and fuel system, secondary power, etc.
Design features of Lockheed L-2000 supersonic transport
ASME -- Paper
ASME Meeting AV-39 ; 1965 Supersonic
1965
12 pages
Conference paper
English
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