Experiments on Shock-Wave/Boundary-Layer Interactions Produced by Two-Dimensional Ramps and Three-Dimensional Obstacles

Experiments on shock-wave/boundary-layer interactions have been executed on a two-dimensional ramp at Mach numbers 10 and 5 and on a three-dimensional obstacle at Mach number 10. Reynolds number effect has been examined for interactions at Mach 5. In order to reproduce the ratio of the wall temperature to the recovery temperature of the real flight the model could be cooled by circulation of liquid nitrogen. The flow produced have been investigated by means of schlieren photographs, surface flow visualizations, thermosensitive painting, surface heat transfer and surface pressure measurements.