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

[+] Author and Article Information
L. H. Back, R. F. Cuffel, P. F. Massier

Jet Propulsion Laboratory, California Institute of Technology, Pasadena, Calif.

J. Heat Transfer 92(3), 333-344 (Aug 01, 1970) (12 pages) doi:10.1115/1.3449668 History: Received June 09, 1969; Online August 11, 2010


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 /ρe ue2) (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.

Copyright © 1970 by ASME
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