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Combustion performance and heat transfer characterization of LOX/hydrocarbon type propellants, volume 2A data base which relates candidate design variables, such as injector type, acoustic cavity configuration, chamber length, fuel film-cooling, etc., to operational characteristics such as combustion efficiency, combustion stability, carbon deposition, and chamber gas-side heat flux was generated.
Document ID
19840003250
Document Type
Contractor Report (CR)
Authors
Schoenman, L. (Aerojet Liquid Rocket Co. Sacramento, CA, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1983
Subject Category
PROPELLANTS AND FUELS
Report/Patent Number
NAS 1.26:171714
REPT-15958T-1548-MA-129T-003F
NASA-CR-171714
Funding Number(s)
CONTRACT_GRANT: NAS9-15958
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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NameType 19840003250.pdf STI