Ejector was investigated in unheated quiescent air facility over range of operational variables applicable to Mach 2.5 aircraft; 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 transonic flight Mach number region from 0.9 to 1.1, where ratio decreased to 0.945 for ejector corrected weight flow ratio of 0.105.
Internal-performance of two-position divergent shroud ejector
NASA -- Tech Note
1961
19 pages
Report
English
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Internal-performance evaluation of two fixed-divergent shroud ejectors
Engineering Index Backfile | 1961
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