ISSN Online: 2377-424X
International Heat Transfer Conference 3
SHOCK WAVE−BOUNDARY LAYER INTERACTION
Sinopsis
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.