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Performance characteristics of aircraft cooling ejectors having short cylindrical shroudsThe factors affecting the performance of ejector suitable for aircraft cooling are investigated theoretically and experimentally. The investigation covers a range of shroud-to-nozzle diameter ratios from 1.1 to 1.6, of shroud lengths from 0.2 to 2.28 nozzle diameters, of secondary-to-primary weight-flow ratios from 0 to 0.12, and of ambient-to-nozzle pressure ratios from 0.7 to 0.06. The results of a simplified theoretical analysis based on each type of flow are in good agreement with those experimentally obtained.
Document ID
19930086635
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Kochendorfer, Fred D
Rousso, Morris D
Date Acquired
August 16, 2013
Publication Date
May 22, 1951
Report/Patent Number
NACA-RM-E51E01
Accession Number
93R15925
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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