Ejectors for Mach 2.2 aircraft were evaluated over range of primary pressure and ejector corrected weight flow ratios; designs differed about 16% in shroud longitudinal spacing ratio; for corrected weight flow ratios up to 0.10, performance of designs is comparable with that of similar continuously variable ejector except at conditions corresponding to acceleration with afterburning from Mach 0.4 to 1.2.
Internal-performance evaluation of two fixed-divergent shroud ejectors
NASA -- Tech Note
1961
30 pages
Report
English
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