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.


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    Title :

    Internal-performance evaluation of two fixed-divergent shroud ejectors


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1961


    Size :

    30 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English