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.


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    Titel :

    Internal Performance Evaluation of a Two Position Divergent Shroud Ejector


    Beteiligte:
    J. R. Mihaloew (Autor:in) / A. J. Stofan (Autor:in)

    Erscheinungsdatum :

    1960


    Format / Umfang :

    24 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Internal-performance of two-position divergent shroud ejector

    Mihaloew, J.R. / Stofan, A.J. | Engineering Index Backfile | 1961


    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