Knowledge of rate of heat transfer to walls of supersonic nozzles is desirable for design of rocket nozzles and of hypersonic wind tunnel nozzles; heat transfer to such nozzle is boundary layer problem with variable free stream velocity; approximate solution given for case of turbulent boundary layer.


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    Title :

    Heat transfer to incompressible turbulent boundary layer and estimation of heat-transfer coefficients at supersonic nozzle throats


    Additional title:

    J Aeronautical Sciences


    Contributors:


    Publication date :

    1956


    Size :

    11 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :