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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    Title :

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


    Additional title:

    NASA -- Tech Note


    Contributors:
    Bloomer, H.E. (author) / Antl, R.J. (author) / Renas, P.E. (author)


    Publication date :

    1961


    Size :

    61 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :




    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