NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Laser Schlieren and ultraviolet diagnostics of rocket combustionA low pressure oxygen/hydrogen turbine drive combustor hot-fire test series was conducted on the Turbine Drive Combustor Technology Program. The first objective was to gather data on an axisymmetric combustion system to support anchoring of a new combustion/fluid dynamics computer code under development on the same contract. The second objective was to gain insight into low mixture ratio combustion characteristics of coaxial injector elements.
Document ID
19850018600
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Fisher, S. C. (Rockwell International Corp. Canoga Park, CA, United States)
Date Acquired
August 12, 2013
Publication Date
April 1, 1985
Publication Information
Publication: NASA. Marshall Space Flight Center Advan. High Pressure O2(H2 Technol.
Subject Category
Inorganic And Physical Chemistry
Accession Number
85N26911
Funding Number(s)
CONTRACT_GRANT: NAS8-34728
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

IDRelationTitle19850018551Collected WorksAdvanced High Pressure O2/H2 Technology
No Preview Available