Laminarization of a Turbulent Boundary Layer in Nozzle Flow—Boundary Layer and Heat Transfer Measurements With Wall Cooling

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  • L. H. Back
    Jet Propulsion Laboratory, California Institute of Technology, Pasadena, Calif.
  • R. F. Cuffel
    Jet Propulsion Laboratory, California Institute of Technology, Pasadena, Calif.
  • P. F. Massier
    Jet Propulsion Laboratory, California Institute of Technology, Pasadena, Calif.

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<jats:p>Boundary layer and heat transfer measurements are presented for flow through a cooled, conical nozzle with a convergent and divergent half-angle of 10 deg for a wall-to-total-gas temperature ratio of about 0.5. A reduction in heat transfer below values typical of a turbulent boundary layer was found when values of the parameter K = (μe/ρeue2) (due/dx) exceeded about 2 to 3 × 10−6. The boundary layer measurements, when viewed in conjunction with the heat transfer measurements, reveal the complicated nature of the flow and thermal behavior and their interrelationship when laminarization occurs.</jats:p>

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