Shock Wave-Boundary Layer Interaction on the Non-adiabatic Ramp Surface

The boundary layer separation of the supersonic air flow over the heated compression ramp has been investigated. Particle Image Velocimetry and Shlieren non-invasive visualization methods were used to study the influence of surface heating on the structure of separation zone. The linear dependence of separation length on the temperature ratio was found. The influence of surface heating on separation region instability was studied. It was found experimentally that increase of wall temperature causes intensification of separation region fluctuations.