A two-position divergent shroud ejector was investigated in an unheated quiescent-air facility over a range of operational variables applicable to a Mach 2.5 aircraft. The performance data are shown in terms of hypothetical engine operating conditions to illustrate variations of performance with Mach number. The overall thrust performance was reasonably good, with ejector thrust ratios ranging from 0.97 to 0.98 for all conditions except that corresponding to acceleration with afterburning through the transonic flight Mach number region from 0.9 to 1.1, where the ejector thrust ratio decreased to as low as 0.945 for an ejector corrected weight-flow ratio of 0.105.
Internal Performance Evaluation of a Two Position Divergent Shroud Ejector
1960-01-01
Report
No indication
English
Internal-performance of two-position divergent shroud ejector
Engineering Index Backfile | 1961
|Internal-performance evaluation of two fixed-divergent shroud ejectors
Engineering Index Backfile | 1961
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