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Combustion effects on film coolingThe effects of: (1) a reactive environment on film cooling effectiveness, and (2) film cooling on rocket engine performance were determined experimentally in a rocket thrust chamber assembly operating with hydrogen and oxygen propellants at 300 psi chamber pressure. Tests were conducted using hydrogen, helium, and nitrogen film coolants in an instrumented, thin walled, steel thrust chamber. The film cooling, performance loss, and heat transfer coefficient data were correlated with the ALRC entrainment film cooling model which relates film coolant effectiveness and mixture ratio at the wall to the amount of mainstream gases entrained with the film coolant in a mixing layer. In addition, a comprehensive thermal analysis computer program, HOCOOL, was prepared from previously existing ALRC computer programs and analytical techniques.
Document ID
19770014416
Document Type
Contractor Report (CR)
Authors
Rousar, D. C. (Aerojet Liquid Rocket Co. Sacramento, CA, United States)
Ewen, R. L. (Aerojet Liquid Rocket Co. Sacramento, CA, United States)
Date Acquired
September 3, 2013
Publication Date
February 24, 1977
Subject Category
FLUID MECHANICS AND HEAT TRANSFER
Report/Patent Number
NASA-CR-135052
Funding Number(s)
CONTRACT_GRANT: NAS3-17813
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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