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ISSN Online: 2377-424X

International Heat Transfer Conference 3
August, 7-12, 1966, Chicago, USA

INFLUENCE OF TEMPERATURE RATIO ON HEAT TRANSFER TO A FLAT PLATE THROUGH A TURBULENT BOUNDARY LAYER IN AIR

Get access (open in a dialog) DOI: 10.1615/IHTC3.1770
pages 41-49

Sinopsis

The Stanton number of a smooth flat plate exposed to a longitudinal stream of gas depends mainly on the Reynolds number, on the Mach number and on the ratio of plate temperature to gas-stream temperature. Although many theoretically-based expressions have been derived for the Stanton-number function, the influences of the Mach number and of the temperature ratio have remained uncertain. This paper provides a simple recommendation for the Stanton number: by examination of experimental data for air, it is shown that the Stanton number can be taken as equal to 1.16 times one half of the drag coefficient, the latter quantity being calculated by a procedure presented by the authors on an earlier occasion_[1].

The data examined are of two kinds:—

(i) Experimental data on heat transfer from isothermal flat plates through turbulent boundary layers of air, from eleven earlier publications: they show no appreciable dependence of the Reynolds-analogy factor (twice Stanton number divided by drag coefficient) on Mach number, Reynolds number or temperature ratio.

(ii) The authors' own experiments, by a transient technique, in a low-Mach-number wind tunnel, with stream temperature between 2.7 and 1 times the plate temperature: these experiments also support the recommendation for the Stanton number function.