On the influence of elevated surface temperatures on hypersonic shock wave/boundary layer interaction at a heated ramp model

摘要: Although important flow parameters as Mach number, Reynolds number and total enthalpy can be reproduced in most hypersonic experiments quite well, due to different surface temperature effects wind tunnel flight, scaling well specific properties of shock wave/boundary layer interactions are different. This especially holds for short-duration facilities like, e.g. tunnels where short running times the models remain more or less at ambient temperature. To overcome this shortcoming, an experimental study has been conducted using a preheatable ramp model with 15° angle. allowed us adjust surfaces arbitrary just before experiment started. Pressure heat flux measurements clearly showed effect varying free stream temperatures. These results supported by schlieren pictures infrared measurements. The comparison theoretical numerical shows good agreement. Separation bubble laws proposed Katzer Davis have applied partially confirmed local conditions boundary separation.