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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    Title :

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


    Additional title:

    NASA -- Memo


    Contributors:


    Publication date :

    1959


    Size :

    53 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


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