Established turbulent boundary-layer methods for predicting throat heat fluxes are often conservative by factors of two or more when applied to low-thrust rocket engines; wall-temperature data from liquid-rocket tests employing three nozzle contours in 20- to 100-lb thrust, 100- to 3000-psia chamber-pressure range, with various injectors are presented; it is shown that thermal wall conditions can be predicated by means of local convective heat-transfer coefficients, calculated from Colburn flat-plate relation for laminar flow; method of obtaining reference position for length parameter in Reynolds number is suggested; approach provides data correlation in transonic and supersonic flow regions. (07552)


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    Title :

    Laminar boundary-layer heat transfer in low-thrust rocket nozzles


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Schoenman, L. (author) / Block, P. (author)

    Published in:

    Publication date :

    1968


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English