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.


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    Title :

    Internal-performance of two-position divergent shroud ejector


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1961


    Size :

    19 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English





    Internal Performance Evaluation of a Two Position Divergent Shroud Ejector

    Mihaloew, James R. / Stofan, Andrew J. | NTRS | 1960


    Internal-perfomance evaluation of a two-position divergent shroud ejector

    Mihaloew, James R. / Stofan, Andrew J. | TIBKAT | 1961


    Internal Performance of Several Divergent-Shroud Ejector Nozzles with High Divergence Angles

    Trout, Arthur M. / Papell, S. Stephen / Povolny, John H. | NTRS | 1957


    Internal-performance evaluation of two fixed-divergent shroud ejectors

    Mihaloew, J.R. | Engineering Index Backfile | 1961