Thrust, boundary layer, and heat transfer characteristics were computed for exhaust nozzles for propulsion device, having radial flow in divergent part; results were generalized independent of divergence angle and of stagnation pressure in temperature range of 1000 to 3000 C; means of determining aerodynamically optimum wall is provided.


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    Titel :

    Estimated performance of radial-flow exit nozzles for air in chemical equilibrium


    Weitere Titelangaben:

    NASA -- Memo


    Beteiligte:


    Erscheinungsdatum :

    1959


    Format / Umfang :

    53 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


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