Nozzles with divergence angles of 15, 25 and 29° were tested at area ratios of 10, 25, and 40 at pressure ratios up to 120; sizable thrust gains could be realized by optimizing divergence angle at given surface area ratio; simplified method of thrust determination for conical nozzles permits calculation of thrust in separated flow region from unseparated static-pressure distributions.


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    Title :

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


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1960


    Size :

    31 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :