Determination of performance and flow separation characteristics; variables include divergent half-angles from 15 to 30°, area ratios from 8/1 to 75/1, and pressure ratios from 35 to 840; results showed that 20 or 25° half-angles were superior to vacuum conditions; advantage of these over smaller area ratio, 15° half-angle nozzles amounted to about 1% in thrust coefficient.


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    Titel :

    Experimental study of effects of geometric variables on performance of conical rocket-engine exhaust nozzles


    Weitere Titelangaben:

    NASA -- Tech Note


    Beteiligte:
    Bloomer, H.E. (Autor:in) / Antl, R.J. (Autor:in) / Renas, P.E. (Autor:in)


    Erscheinungsdatum :

    1961


    Format / Umfang :

    61 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :




    Performance of several conical convergent-divergent rocket-type exhaust nozzles

    Campbell, C.E. / Farley, J.M. | Engineering Index Backfile | 1960



    Performance of plug-type rocket exhaust nozzles

    Berman, K. / Crimp, Jr., F.W. | Engineering Index Backfile | 1961