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Preliminary engineering report for design of a subscale ejector/diffuser system for high expansion ratio space engine testingThe design of a subscale jet engine driven ejector/diffuser system is examined. Analytical results and preliminary design drawings and plans are included. Previously developed performance prediction techniques are verified. A safety analysis is performed to determine the mechanism for detonation suppression.
Document ID
19840023203
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Wojciechowski, C. J. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Kurzius, S. C. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Doktor, M. F. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Date Acquired
September 4, 2013
Publication Date
April 1, 1984
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.26:171137
NASA-CR-171137
LMSC-HREC-TR-D951414
Report Number: NAS 1.26:171137
Report Number: NASA-CR-171137
Report Number: LMSC-HREC-TR-D951414
Accession Number
84N31273
Funding Number(s)
CONTRACT_GRANT: NAS8-35051
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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