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Heat Transfer Research
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ISSN Imprimer: 1064-2285
ISSN En ligne: 2162-6561

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Heat Transfer Research

DOI: 10.1615/HeatTransRes.v33.i3-4.20
4 pages

Experimental Study of Heat Transfer in a Strongly Cooled Boundary Layer in Supersonic Air Flow

E. V. Gurentsov
Heat Transfer Division IVTAN (Institute of High Temperatures) Scientific Association Russian Academy of Sciences 13/19, Izhorskaya Street Moscow, 127412 Russia
V. K. Shikov
Institute for High Temperatures, Russian Academy of Sciences, Moscow, Russia
E. B. Eigenson
Heat Transfer Division IVTAN (Institute of High Temperatures) Scientific Association Russian Academy of Sciences 13/19, Izhorskaya Street Moscow, 127412 Russia

RÉSUMÉ

New experimental data on the laminar-to-turbulent transition characteristics and the turbulent heat transfer were obtained for a strongly cooled boundary layer of supersonic high-temperature air flow on a flat plate with the sharp leading edge. Systematic experiments have been carried out with a shock tube for a wide range of parameters: air flow temperature 1650-6690 К, air flow velocity 1.45-6.45 km/sec, pressure 0.3-5 atm, enthalpy ratio 0.007-0.115, Mach number 1.85-3.5, Reynolds number 5·104-107. Experimental results were compared with Kutateladze-Leontiev theory correlations and with some semiempirical methods of calculation.


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