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Thermal-structural design study of an airframe-integrated ScramjetDesign concepts are developed and evaluated for a cooled structures assembly for the Scramjet engine, for engine subsystems mass, volume, and operating requirements, and for the aircraft/engine interface. A thermal protection system was defined that makes it possible to attain a life of 100 hours and 1000 cycles. The coolant equivalence ratio at the Mach 10 maximum thermal loading condition is 0.6, indicating a capacity for airframe cooling. The mechanical design is feasible for manufacture using conventional materials. For the cooled structures in a six-module engine, the mass per unit capture area is 12.4 KN/sq m. The total weight of a six-module engine assembly including the fuel system is 14.73 KN.
Document ID
19790006874
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Killackey, J. J.
(AiResearch Mfg. Co. Los Angeles, CA, United States)
Katinsky, E. A.
(AiResearch Mfg. Co. Los Angeles, CA, United States)
Tepper, S.
(AiResearch Mfg. Co. Los Angeles, CA, United States)
Vuigner, A. A.
(AiResearch Mfg. Co. Los Angeles, CA, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1978
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIRESEARCH-77-13967
NASA-CR-145368
Accession Number
79N15045
Funding Number(s)
CONTRACT_GRANT: NAS1-13984
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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