Actions for Characteristics of Five Ejector Configurations at Free-Stream Mach Numbers from 0 to 2.0.

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Characteristics of Five Ejector Configurations at Free-Stream Mach Numbers from 0 to 2.0.

Author
Klann, John L.
Published
Aug. 1959.
Physical Description
1 electronic document
Additional Creators
Huff, Ronald G.
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
Thrust, air-handling, and base-pressure characteristics of five ejector configurations were investigated in the Lewis 8-by 6-foot wind tunnel at free-stream Mach numbers from 0 to 2.0 over ranges of primary-jet pressure ratio up to 24 and corrected secondary weight-flow ratio up to 13 percent. The ejector-shroud geometries varied from convergent to divergent. Base pressure ratio and ejector performance were interrelated by means of an exit-momentum parameter. Correlations, to at least a first approximation, with base pressure ratio, of both internal-ejector-flow separation and external-flow separation over the model boattail were shown. Furthermore, it was shown that magnitudes and exact trends in base pressure ratio depended largely, and in a complicated fashion, on ejector geometry and amount of secondary flow. External-stream effects on ejector jet thrust were determined for a typical schedule of jet-engine pressure ratios. With the exception of the ejector having the largest (1.81) shroud-exit-to primary-diameter ratio, there were no stream effects at Mach numbers from 1.5 to 2.0 and variations from quiescent-air thrust data were less than 2.5 percent at the subsonic speed investigated.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19980232933.
NASA-TM-X-23.
Terms of Use and Reproduction
No Copyright.
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