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ISSN Online: 2377-424X

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

SHOCK WAVE−BOUNDARY LAYER INTERACTION

Get access (open in a dialog) DOI: 10.1615/IHTC3.1880
pages 262-273

要約

The results of an experimental investigation of heat transfer and pressure in laminar shock wave−boundary layer interaction corner flow at Mach numbers of 8 and 10 are presented. Following generalized correlations for laminar and turbulent shock wave−boundary layer interaction flow for a Mach number range from 2 to 16 are given. These correlations describe the pressure distribution in terms of plateau pressure and pressure at separation, and, in terms of distance parameters with respect to a characteristic reference line, as functions of Reynolds number, Mach number and pressure ratio. Similarly, correlations for peak heat transfer in the reattachment region for laminar and turbulent flow are established.